Example Airworthiness Directives; Honeywell International Inc. Turbofan Engines

[Federal Register Volume 83, Number 199 (Monday, October 15, 2018)]
[Rules and Regulations]
[Pages 51829-51832]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-22009]
––––––––––––––––––––––––––––––––––
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1116; Product Identifier 2016-NE-32-AD; Amendment 39-19459; AD
2018-21-01]
RIN 2120-AA64
Airworthiness Directives; Honeywell International Inc. Turbofan Engines
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Final rule.
––––––––––––––––––––––––––––––––––
SUMMARY: We are superseding Airworthiness Directive (AD) 2017-20-06 for certain Honeywell
International Inc. (Honeywell) AS907-1-1A turbofan engines. AD 2017-20-06 required a one-time
inspection of the second stage low-pressure turbine (LPT2) blades and, if the blades fail the
inspection, the replacement of the blades with a part eligible for installation. This AD continues to
require a one-time inspection of the LPT2 blades and, if the blades fail the inspection, the
replacement of the blades with a part eligible for installation. This AD was prompted by the need to
clarify the Applicability and Compliance sections of AD 2017-20-06. We are issuing this AD to
address the unsafe condition on these products.
DATES: This AD is effective November 19, 2018.
The Director of the Federal Register approved the incorporation by reference of a certain
publication listed in this AD as of November 9, 2017 (82 FR 46379, October 5, 2017).
ADDRESSES: For service information identified in this final rule, contact Honeywell International
Inc., 111 S 34th Street, Phoenix, AZ 85034-2802; phone: 800-601-3099; internet:
https://myaerospace2.honeywell.com/wps/portal. You may view this service information at the FAA,
Engine and Propeller Standards Branch, 1200 District Avenue, Burlington, MA 01803. For
information on the availability of this material at the FAA, call 781-238-7759. It is also available on
the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2017-1116.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for
and locating Docket No. FAA-2017-1116; or in person at Docket Operations between 9 a.m. and 5
p.m., Monday through Friday, except Federal holidays. The AD docket contains this final rule, the
1

regulatory evaluation, any comments received, and other information. The address for Docket
Operations (phone: 800-647-5527) is U.S. Department of Transportation, Docket Operations, M-30,
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, Washington, DC
20590.
FOR FURTHER INFORMATION CONTACT: Joseph Costa, Aerospace Engineer, Los Angeles
ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax:
562-627-5210; email: joseph.costa@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD
2017-20-06, Amendment 39-19063 (82 FR 46379, October 5, 2017), (“AD 2017-20-06”). AD 201720-06 applied to certain Honeywell International Inc. (Honeywell) AS907-1-1A turbofan engines.
The NPRM published in the Federal Register on January 30, 2018 (83 FR 4167). The NPRM was
prompted by the need to clarify the Applicability and Compliance sections of AD 2017-20-06. The
NPRM proposed to continue to require one-time inspection of the LPT2 blades and, if the blades fail
the inspection, the replacement of the blades with a part eligible for installation. We are issuing this
AD to address the unsafe condition on these products.
Comments
We gave the public the opportunity to participate in developing this AD. The following presents
the comments received on the NPRM and the FAA's response to each comment.
Request To Align the Compliance Requirements With the Service Bulletin (SB)
Bombardier Aerospace (Bombardier) requested that the compliance requirements of the AD be
aligned with Honeywell SB AS907-72-9067, Revision 1, dated March 20, 2017. Bombardier asked
that we remove the requirements for measured wear requirements for recording of wear. Bombardier
noted that Honeywell SB AS907-72-9067 requires contact between the LPT2 rotor blade Z-gap.
We disagree. Honeywell SB AS907-72-9067, Revision 1, dated March 20, 2017 and the
compliance section of this AD provide the same guidance for measuring and recording wear with a
borescope at the LPT2 blade shroud Z-gap. Reported borescope inspections of high-time engines
show that blade-to-blade contact at the Z-gap is difficult to measure with a borescope. The FAA and
Honeywell agree that the measured wear limit of 0.005”, as defined by the Honeywell Light
Maintenance Manual (LMM) AS907-1-1A, 72-00-00, is acceptable for this AD.
Additionally, the FAA disagrees with the request to remove the requirement for recordings of the
borescope inspection. We find that making these recordings with a clean digital image helps us to
identify wear characteristics, severity, and cumulative damage of LPT2 blade assembly and to
provide future borescope requirements for LPT blade maintenance. We did not change this AD.
Request To Revise Costs of Compliance
Bombardier Aerospace requested that we align the cost estimates in this AD with the cost
estimates in Honeywell's SB.
We disagree. The slight differences in costs between the NPRM and Honeywell's SB reflect the
additional recording requirements in this AD. We did not change this AD.

2

Revision to Applicability
The intent of the NPRM was to limit the applicability of this AD to affected blades that have
more than 8,000 hours since new on November 9, 2017 (the effective date of AD 2017-20-06). We
therefore revised the applicability to refer to “November 9, 2017,” instead of “the effective date of
this AD.”
Conclusion
We reviewed the relevant data, considered the comments received, and determined that air safety
and the public interest require adopting this AD as proposed.
Related Service Information Under 1 CFR Part 51
We reviewed Honeywell SB AS907-72-9067, Revision 1, dated March 20, 2017. This SB
describes procedures for inspecting the LPT2 blades. This service information is reasonably available
because the interested parties have access to it through their normal course of business or by the
means identified in the ADDRESSES section.
Other Related Service Information
We reviewed Honeywell SB AS907-72-9067, Revision 0, dated December 12, 2016, which also
describes procedures for inspecting the LPT2 blades. We also reviewed the Honeywell LMM AS9071-1A, 72-00-00, Section 72-05-12, dated May 25, 2016, and Section 72-55-03, dated September 27,
2011, which provide additional guidance for performing borescope inspections.
Costs of Compliance
We estimate that this AD affects 40 engines installed on airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
Action

Labor cost

Parts
cost

Borescope inspection 10 work-hours × $85 per
hour = $850
Report results of
inspection

Cost per
product

Cost on U.S.
operators

$0

$850

$34,000

0

85

3,400

1 work-hour × $85 per hour
= $85

We estimate the following costs to do any necessary replacements that would be required based
on the results of the inspection. We estimate that 40 engines will need this replacement.
On-Condition Costs
Action
Replacement of the LPT2 blade
set

Labor cost
50 work-hours × $85 per hour =
$4,250

3

Parts
cost
$50,000

Cost per
product
$54,250

Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor
shall a person be subject to a penalty for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that collection of information displays a
currently valid OMB Control Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour
per response, including the time for reviewing instructions, searching existing data sources, gathering
and maintaining the data needed, completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Send comments regarding this burden
estimate or any other aspect of this collection of information, including suggestions for reducing this
burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to issue rules on aviation safety.
Subtitle I, Section 106, describes the authority of the FAA Administrator. Subtitle VII, Aviation
Programs, describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in Subtitle VII, Part A, Subpart III,
Section 44701, “General requirements.” Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices,
methods, and procedures the Administrator finds necessary for safety in air commerce. This
regulation is within the scope of that authority because it addresses an unsafe condition that is likely
to exist or develop on products identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the Executive Director, Aircraft
Certification Service, as authorized by FAA Order 8000.51C. In accordance with that order, issuance
of ADs is normally a function of the Compliance and Airworthiness Division, but during this
transition period, the Executive Director has delegated the authority to issue ADs applicable to
engines, propellers, and associated appliances to the Manager, Engine and Propeller Standards
Branch, Policy and Innovation Division.
Regulatory Findings
We have determined that this AD will not have federalism implications under Executive Order
13132. This AD will not have a substantial direct effect on the States, on the relationship between the
national government and the States, or on the distribution of power and responsibilities among the
various levels of government.
For the reasons discussed above, I certify that this AD:
(1) Is not a “significant regulatory action” under Executive Order 12866,
(2) Is not a “significant rule” under DOT Regulatory Policies and Procedures (44 FR 11034,
February 26, 1979),
(3) Will not affect intrastate aviation in Alaska, and
(4) Will not have a significant economic impact, positive or negative, on a substantial number of
small entities under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety.

4

Adoption of the Amendment
Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR
part 39 as follows:
PART 39–AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13 [Amended]
2. The FAA amends § 39.13 by removing Airworthiness Directive (AD) 2017-20-06, Amendment
39-19063 (82 FR 46379, October 5, 2017), and adding the following new AD:

5

AIRWORTHINESS
DIRECTIVE

FAA
Aviation Safety

www.faa.gov/aircraft/safety/alerts/
www.gpoaccess.gov/fr/advanced.html

2018-21-01 Honeywell International Inc.: Amendment 39-19459; Docket No. FAA-2017-1116;
Product Identifier 2016-NE-32-AD.
(a) Effective Date
This AD is effective November 19, 2018.
(b) Affected ADs
This AD replaces AD 2017-20-06, Amendment 39-19063 (82 FR 46379, October 5, 2017).
(c) Applicability
This AD applies to Honeywell International Inc. (Honeywell) AS907-1-1A turbofan engines
with second stage low-pressure turbine (LPT2) rotor blades, part number 3035602-1, installed, that
have more than 8,000 hours since new on November 9, 2017 (the effective date of AD 2017-20-06).
(d) Subject
Joint Aircraft System Component (JASC) Code 7250 Turbine Section.
(e) Unsafe Condition
This AD was prompted by reports of loss of power due to failure of the LPT2 blade. We are
issuing this AD to prevent failure of the LPT2 blades. The unsafe condition, if not corrected, could
result in failure of one or more engines and loss of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified, unless already done.
(g) Required Actions
Within 200 hours time in service after the effective date of this AD, do the following:
(1) Perform a one-time borescope inspection for wear of the Z gap contact area at the blade tip
shroud for each of the 62 LPT2 rotor blades. Use the Accomplishment Instructions, Paragraph
3.B.(1), of Honeywell Service Bulletin (SB) AS907-72-9067, Revision 1, dated March 20, 2017, to
do the inspection.
(2) If the measured wear and/or fretting of any Z gap contact area is greater than 0.005 inch,
replace the LPT2 rotor assembly with a part eligible for installation before further flight.
(3) Using a borescope, make a clear digital image of the Z gap contact area at the blade tip
shroud of the 62 LPT2 rotor blades, and do the following:
(i) Identify the three Z gap contact areas with the greatest amount of wear and/or fretting.

6

(ii) Record the blade position on the LPT2 rotor assembly and the measured wear of the three Z
gap contact areas with the greatest amount of wear and/or fretting.
(iii) Send the results to Honeywell at engine.reliability@honeywell.com within 30 days after
completing these actions.
(h) Credit for Previous Actions
You may take credit for the actions required by paragraphs (g)(1) and (2) of this AD if you
performed these actions before the effective date of this AD using Honeywell SB AS907-72-9067,
Revision 0, dated December 12, 2016.
(i) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not required to respond to, nor
shall a person be subject to a penalty for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that collection of information displays a
currently valid OMB Control Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is estimated to be approximately 1 hour
per response, including the time for reviewing instructions, searching existing data sources, gathering
and maintaining the data needed, completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Send comments regarding this burden
estimate or any other aspect of this collection of information, including suggestions for reducing this
burden to: Information Collection Clearance Officer, Federal Aviation Administration, 10101
Hillwood Parkway, Fort Worth, TX 76177-1524.
(j) Alternative Methods of Compliance (AMOCs)
(1) The Manager, Los Angeles ACO Branch, FAA, may approve AMOCs for this AD, if
requested using the procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, send your
request to your principal inspector or local Flight Standards District Office, as appropriate. If sending
information directly to the manager of the Los Angeles ACO Branch, send it to the attention of the
person identified in paragraph (k) of this AD. You may email your request to: 9-ANM-LAACOAMOC-REQUESTS@faa.gov.
(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a
principal inspector, the manager of the local flight standards district office/certificate holding district
office.
(k) Related Information
For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles
ACO Branch, FAA, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax:
562-627-5210; email: joseph.costa@faa.gov.
(l) Material Incorporated by Reference
(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the
service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do the actions required by this AD,
unless the AD specifies otherwise.
(3) The following service information was approved for IBR on November 9, 2017 (82 FR
46379, October 5, 2017).
(i) Honeywell Service Bulletin AS907-72-9067, Revision 1, dated March 20, 2017.
7

(ii) Reserved.
(4) For Honeywell service information identified in this AD, contact Honeywell International
Inc., 111 S 34th Street, Phoenix, AZ 85034-2802; phone: 800-601-3099; internet:
https://myaerospace2.honeywell.com/wps/portal.
(5) You may view this service information at FAA, Engine and Propeller Standards Branch,
1200 District Avenue, Burlington, MA 01803. For information on the availability of this material at
the FAA, call 781-238-7759.
(6) You may view this service information that is incorporated by reference at the National
Archives and Records Administration (NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Burlington, Massachusetts, on October 3, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch,
Aircraft Certification Service.

8