81 FR 67100 - Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 190 (September 30, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 190 (September 30, 2016)
| Page Range | 67100-67102 | |
| FR Document | 2016-23263 |
[Federal Register Volume 81, Number 190 (Friday, September 30, 2016)] [Rules and Regulations] [Pages 67100-67102] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-23263] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-4866; Directorate Identifier 2015-NE-33-AD; Amendment 39-18648; AD 2016-18-17] RIN 2120-AA64 Airworthiness Directives; Honeywell International Inc. Turboprop and Turboshaft Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Final rule. ----------------------------------------------------------------------- SUMMARY: We are adopting a new airworthiness directive (AD) for certain Honeywell International Inc. (Honeywell) TPE331 model turboprop engines and TSE331-3U model turboshaft engines. This AD was prompted by the discovery of cracks in a 2nd stage compressor impeller during a routine shop visit. This AD requires removal of the 2nd stage compressor impeller. We are issuing this AD to prevent failure of the compressor impeller, uncontained part release, damage to the engine, and damage to the airplane. DATES: This AD is effective November 4, 2016. 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-2015- 4866; or in person at the Docket Management Facility between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains this AD, the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647- 5527) is Document Management Facility, 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 [[Page 67101]] Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562- 627-5246; fax: 562-627-5210; email: [email protected]. SUPPLEMENTARY INFORMATION: Discussion We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 by adding an AD that would apply to certain Honeywell TPE331 model turboprop engines and TSE331-3U model turboshaft engines. The NPRM published in the Federal Register on March 15, 2016 (81 FR 13764) (``the NPRM''). The NPRM was prompted by the discovery of cracks in a 2nd stage compressor impeller during a routine shop visit. The NPRM proposed to require removal of the 2nd stage compressor impeller. We are issuing this AD to prevent failure of the compressor impeller, uncontained part release, damage to the engine, and damage to the airplane. 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 Change Compliance Bearskin Airlines and Turbine Standard, LTD requested that the compliance time interval be changed because many TPE331 engine operators are on a Continuous Airworthiness Maintenance (CAM) program. This program does not require impeller inspections per the overhaul manual and the impeller is not considered as ``overhauled''. AD compliance under CAM may be interpreted as being within 200 cycles or 30 to 45 days. Other commenters requested that the compliance time be changed to a less aggressive time interval appropriate to the unsafe condition. Many high-usage operators have suspect impellers that currently exceed 7,000 cycles since the last compressor inspection. We agree. We changed compliance interval in paragraph (e)(1) of this AD. Request To Allow Other Inspection Facilities To Return Impellers to Service Turbine Standard, LTD requested that this AD allow other inspection facilities to return impellers to service. There are many inspection facilities that are capable of inspecting the 2nd stage compressor impeller. We partially agree. We agree that many inspection facilities are capable of performing a focused inspection of the 2nd stage compressor impeller. We disagree with allowing other inspection and regrinding facilities to return impellers to service. This AD does not address inspection or regrinding of the curvic area of the 2nd stage compressor impeller. Regrinding of the curvic area of the 2nd stage compressor impeller involves machining of a critical rotating part, which must be approved by the FAA. We did not change this AD. Request To Change Costs of Compliance Honeywell; Perimeter Aviation, LP; and Intercontinental Jet Service Corp. requested that the costs of compliance be changed because the NPRM is not representative of the impeller's replacement costs. Honeywell quotes the cost of a new 2nd stage compressor impeller at $11,922.50. We partially agree. We agree with the comment because the costs were not clearly defined. We disagree with the comment because replacement costs are based on pro-rated costs that are estimated at 50% of new parts costs. Since issuing the NPRM, the FAA estimated that 30% of impellers will be scrapped; therefore, we changed the costs of compliance accordingly. Request To Include Service Information The European Aviation Safety Agency, Honeywell, and Candler & Associates, Inc. requested that service information be included in this AD. Having the service information available would aid in understanding any differences between this AD and the service information. We agree. We added Honeywell Service Bulletin (SB) TPE331-72-2208, dated July 29, 2014, as related information in 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 with the changes described previously. We also determined that these changes will not increase the economic burden on any operator or increase the scope of this AD. Related Service Information We reviewed Honeywell SB TPE331-72-2208, dated July 29, 2014. The SB describes procedures for replacing the 2nd stage compressor impeller. Costs of Compliance We estimate that this AD will affect 4,000 engines installed on airplanes of U.S. registry. We estimate that it will take 2 hours per engine to comply with this AD. The average labor rate is $85 per hour. We also estimate that required parts will cost about $4,404.50 per engine. Based on these figures, we estimate the total cost of this AD on U.S. operators to be $18,298,000. 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. Regulatory Findings 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 to the extent that it justifies making a regulatory distinction, 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. Adoption of the Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows: [[Page 67102]] PART 39--AIRWORTHINESS DIRECTIVES 0 1. The authority citation for part 39 continues to read as follows: Authority: 49 U.S.C. 106(g), 40113, 44701. Sec. 39.13 [Amended] 0 2. The FAA amends Sec. 39.13 by adding the following new airworthiness directive (AD): 2016-18-17 Honeywell International Inc. (Type Certificate Previously Held by AlliedSignal Inc., Garrett Engine Division; Garrett Turbine Engine Company; and AiResearch Manufacturing Company of Arizona): Amendment 39-18648; Docket No. FAA-2015-4866; Directorate Identifier 2015-NE-33-AD. (a) Effective Date This AD is effective November 4, 2016. (b) Affected ADs None. (c) Applicability This AD applies to Honeywell International Inc. (Honeywell) TPE331-3U, -3UW, -5, -5A, -5AB, -5B, -6, -6A, -8, -10, -10AV, -10GP, -10GT, -10N, -10P, -10R, -10T, -10U, -10UA, -10UF, -10UG, -10UGR, - 10UR, and -11U model turboprop engines, and TSE331-3U model turboshaft engines, with a 2nd stage compressor impeller, part number (P/N) 893482-1 through -5, inclusive, or P/N 3107056-1 or P/N 3107056-2, installed. (d) Unsafe Condition This AD was prompted by the discovery of cracks in a 2nd stage compressor impeller during a routine shop visit. We are issuing this AD to prevent failure of the compressor impeller, uncontained part release, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) Remove from service the 2nd stage compressor impeller at next removal of the 2nd stage compressor impeller from the engine or before exceeding 11,500 cycles in service after the effective date of this AD, whichever occurs first. (2) Reserved. (f) Installation Prohibition After the effective date of this AD, do not install a 2nd stage compressor impeller, part number (P/N) 893482-1 through -5, inclusive, or P/N 3107056-1 or P/N 3107056-2, into any engine. (g) Alternative Methods of Compliance (AMOCs) The Manager, Los Angeles Aircraft Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. (h) Related Information (1) For more information about this AD, contact Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562-627-5246; fax: 562-627-5210; email: [email protected]. (2) Honeywell SB TPE331-72-2208, dated July 29, 2014, which is not incorporated by reference in this AD, can be obtained from Honeywell, using the contact information in paragraph (h)(3) of this AD. (3) 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://myaerospace.honeywell.com/wps/portal/!ut/. (4) You may view this service information at FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. (i) Material Incorporated by Reference None. Issued in Burlington, Massachusetts, on August 26, 2016. Colleen M. D'Alessandro, Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2016-23263 Filed 9-29-16; 8:45 am] BILLING CODE 4910-13-P
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that is likely to exist or develop on (d) Unsafe Condition (i) Material Incorporated by Reference
products identified in this rulemaking This AD was prompted by reports of cracks None.
action. found on the seal teeth of the HPC stage 8– Issued in Burlington, Massachusetts, on
10 spool. We are issuing this AD to prevent September 26, 2016.
Regulatory Findings failure of the HPC stage 8–10 spool,
Colleen M. D’Alessandro,
This AD will not have federalism uncontained rotor release, damage to the
implications under Executive Order engine, and damage to the airplane. Manager, Engine & Propeller Directorate,
Aircraft Certification Service.
13132. This AD will not have a (e) Compliance
substantial direct effect on the States, on [FR Doc. 2016–23740 Filed 9–29–16; 8:45 am]
Comply with this AD within the
the relationship between the national compliance times specified, unless already
BILLING CODE 4910–13–P
government and the States, or on the done.
distribution of power and (1) Perform an eddy current inspection
responsibilities among the various DEPARTMENT OF TRANSPORTATION
(ECI) or fluorescent penetrant inspection
levels of government. (FPI) of the seal teeth of the HPC stage 8–10 Federal Aviation Administration
For the reasons discussed above, I spool as follows:
certify that this AD: (i) For HPC stage 8–10 spools with fewer
14 CFR Part 39
(1) Is not a ‘‘significant regulatory than 11,000 cycles since new (CSN) on the
action’’ under Executive Order 12866, effective day of this AD, inspect at the next [Docket No. FAA–2015–4866; Directorate
(2) Is not a ‘‘significant rule’’ under shop visit after reaching 6,000 CSN, not to Identifier 2015–NE–33–AD; Amendment 39–
DOT Regulatory Policies and Procedures exceed 12,500 CSN. 18648; AD 2016–18–17]
(44 FR 11034, February 26, 1979), (ii) For HPC stage 8–10 spools with 11,000
CSN or more on the effective day of this AD, RIN 2120–AA64
(3) Will not affect intrastate aviation
inspect within the next 1,500 cycles in
in Alaska to the extent that it justifies service. Airworthiness Directives; Honeywell
making a regulatory distinction, and (iii) Thereafter, inspect the seal teeth of the International Inc. Turboprop and
(4) Will not have a significant HPC stage 8–10 spool at each shop visit. Turboshaft Engines
economic impact, positive or negative, (2) Remove from service any HPC stage 8–
on a substantial number of small entities 10 spool that fails the ECI or FPI required by
AGENCY: Federal Aviation
under the criteria of the Regulatory paragraph (e)(1) of this AD and replace with Administration (FAA), DOT.
Flexibility Act. a part eligible for installation. ACTION: Final rule.
(3) Guidance on performing the ECI and
List of Subjects in 14 CFR Part 39 the FPI can be found in GE Service Bulletins SUMMARY: We are adopting a new
Air transportation, Aircraft, Aviation (SBs) SB 72–1141 R00, dated December 2, airworthiness directive (AD) for certain
safety, Incorporation by reference, 2015 and SB 72–1142 R00, dated November Honeywell International Inc.
Safety. 30, 2015. (Honeywell) TPE331 model turboprop
(f) Definition engines and TSE331–3U model
Adoption of the Amendment turboshaft engines. This AD was
For the purpose of this AD, an engine shop prompted by the discovery of cracks in
Accordingly, under the authority visit is the induction of an engine into the
delegated to me by the Administrator, shop for maintenance during which the
a 2nd stage compressor impeller during
the FAA amends 14 CFR part 39 as compressor discharge pressure seal face is a routine shop visit. This AD requires
follows: exposed. removal of the 2nd stage compressor
impeller. We are issuing this AD to
PART 39—AIRWORTHINESS (g) Alternative Methods of Compliance prevent failure of the compressor
(AMOCs)
DIRECTIVES impeller, uncontained part release,
The Manager, Engine Certification Office, damage to the engine, and damage to the
■ 1. The authority citation for part 39 FAA, may approve AMOCs for this AD. Use airplane.
continues to read as follows: the procedures found in 14 CFR 39.19 to
make your request. You may email your DATES: This AD is effective November 4,
Authority: 49 U.S.C. 106(g), 40113, 44701. request to: ANE-AD-AMOC@faa.gov. 2016.
§ 39.13 [Amended] (h) Related Information Examining the AD Docket
■ 2. The FAA amends § 39.13 by adding (1) For more information about this AD, You may examine the AD docket on
the following new airworthiness contact John Frost, Aerospace Engineer, the Internet at http://
directive (AD): Engine Certification Office, FAA, 1200 www.regulations.gov by searching for
District Avenue, Burlington, MA 01803; and locating Docket No. FAA–2015–
2016–19–09 General Electric Company:
phone: 781–238–7756; fax: 781–238–7199; 4866; or in person at the Docket
Amendment 39–18658; Docket No.
email: john.frost@faa.gov.
FAA–2016–5307; Directorate Identifier Management Facility between 9 a.m.
(2) GE SB 72–1141, R00, dated December
2016–NE–08–AD.
2, 2015 and GE SB 72–1142, R00, dated and 5 p.m., Monday through Friday,
(a) Effective Date November 30, 2015, which are not except Federal holidays. The AD docket
incorporated by reference in this AD, can be contains this AD, the regulatory
This AD is effective November 4, 2016.
obtained from GE, using the contact evaluation, any comments received, and
(b) Affected ADs information in paragraph (h)(3) of this AD. other information. The address for the
None. (3) For service information identified in Docket Office (phone: 800–647–5527) is
asabaliauskas on DSK3SPTVN1PROD with RULES
this AD, contact General Electric Company, Document Management Facility, U.S.
(c) Applicability GE-Aviation, Room 285, 1 Neumann Way, Department of Transportation, Docket
This AD applies to General Electric Cincinnati, OH 45215, phone: 513–552–3272; Operations, M–30, West Building
Company (GE) GE90–76B, GE90–77B, GE90– email: aviation.fleetsupport@ge.com.
Ground Floor, Room W12–140, 1200
85B, GE90–90B, and GE90–94B turbofan (4) You may view this service information
at the FAA, Engine & Propeller Directorate, New Jersey Avenue SE., Washington,
engines with a high-pressure compressor
(HPC) stage 8–10 spool, part numbers 1200 District Avenue, Burlington, MA. For DC 20590.
1694M80G04, 1844M90G01, or 1844M90G02, information on the availability of this FOR FURTHER INFORMATION CONTACT:
installed. material at the FAA, call 781–238–7125. Joseph Costa, Aerospace Engineer, Los
VerDate Sep<11>2014 18:28 Sep 29, 2016 Jkt 238001 PO 00000 Frm 00010 Fmt 4700 Sfmt 4700 E:\FR\FM\30SER1.SGM 30SER1](https://thefederalregister.org/doc/81_FR_67290/page/1.svg)
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PART 39—AIRWORTHINESS (h) Related Information engine or transmission, and subsequent
DIRECTIVES (1) For more information about this AD, loss of control of the helicopter.
contact Joseph Costa, Aerospace Engineer, DATES: This AD becomes effective
■ 1. The authority citation for part 39 Los Angeles Aircraft Certification Office, October 17, 2016.
FAA, Transport Airplane Directorate, 3960 We must receive comments on this
continues to read as follows:
Paramount Blvd., Lakewood, CA 90712–
Authority: 49 U.S.C. 106(g), 40113, 44701.
AD by November 29, 2016.
4137; phone: 562–627–5246; fax: 562–627–
5210; email: joseph.costa@faa.gov. ADDRESSES: You may send comments by
§ 39.13 [Amended] (2) Honeywell SB TPE331–72–2208, dated any of the following methods:
July 29, 2014, which is not incorporated by • Federal eRulemaking Docket: Go to
■ 2. The FAA amends § 39.13 by adding reference in this AD, can be obtained from http://www.regulations.gov. Follow the
the following new airworthiness Honeywell, using the contact information in online instructions for sending your
directive (AD): paragraph (h)(3) of this AD. comments electronically.
2016–18–17 Honeywell International Inc. (3) For Honeywell service information • Fax: 202–493–2251.
(Type Certificate Previously Held by identified in this AD, contact Honeywell • Mail: Send comments to the U.S.
AlliedSignal Inc., Garrett Engine International Inc., 111 S 34th Street, Phoenix,
AZ 85034–2802; phone: 800–601–3099;
Department of Transportation, Docket
Division; Garrett Turbine Engine Operations, M–30, West Building
Company; and AiResearch Internet: https://
myaerospace.honeywell.com/wps/portal/!ut/. Ground Floor, Room W12–140, 1200
Manufacturing Company of Arizona): New Jersey Avenue SE., Washington,
(4) You may view this service information
Amendment 39–18648; Docket No.
at FAA, Engine & Propeller Directorate, 1200 DC 20590–0001.
FAA–2015–4866; Directorate Identifier
2015–NE–33–AD.
District Avenue, Burlington, MA. For • Hand Delivery: Deliver to the
information on the availability of this ‘‘Mail’’ address between 9 a.m. and 5
(a) Effective Date material at the FAA, call 781–238–7125. p.m., Monday through Friday, except
This AD is effective November 4, 2016. (i) Material Incorporated by Reference Federal holidays.
(b) Affected ADs None. Examining the AD Docket
None. Issued in Burlington, Massachusetts, on You may examine the AD docket on
August 26, 2016. the Internet at http://
(c) Applicability
Colleen M. D’Alessandro, www.regulations.gov by searching for
This AD applies to Honeywell
Manager, Engine & Propeller Directorate, and locating Docket No. FAA–2016–
International Inc. (Honeywell) TPE331–3U, Aircraft Certification Service.
–3UW, –5, –5A, –5AB, –5B, –6, –6A, –8, –10, 9144; or in person at the Docket
–10AV, –10GP, –10GT, –10N, –10P, –10R, [FR Doc. 2016–23263 Filed 9–29–16; 8:45 am] Operations Office between 9 a.m. and 5
–10T, –10U, –10UA, –10UF, –10UG, BILLING CODE 4910–13–P p.m., Monday through Friday, except
–10UGR, –10UR, and –11U model turboprop Federal holidays. The AD docket
engines, and TSE331–3U model turboshaft contains this AD, the Transport Canada
engines, with a 2nd stage compressor DEPARTMENT OF TRANSPORTATION AD, the economic evaluation, any
impeller, part number (P/N) 893482–1 comments received, and other
through –5, inclusive, or P/N 3107056–1 or Federal Aviation Administration information. The street address for the
P/N 3107056–2, installed. Docket Operations Office (telephone
14 CFR Part 39 800–647–5527) is in the ADDRESSES
(d) Unsafe Condition
This AD was prompted by the discovery of [Docket No. FAA–2016–9144; Directorate section. Comments will be available in
cracks in a 2nd stage compressor impeller Identifier 2016–SW–014–AD; Amendment the AD docket shortly after receipt.
during a routine shop visit. We are issuing 39–18667; AD 2016–20–01] For service information identified in
this AD to prevent failure of the compressor this final rule, contact Bell Helicopter
impeller, uncontained part release, damage to RIN 2120–AA64 Textron Canada Limited, 12,800 Rue de
the engine, and damage to the airplane. l’Avenir, Mirabel, Quebec J7J1R4;
Airworthiness Directives; Bell telephone (450) 437–2862 or (800) 363–
(e) Compliance Helicopter Textron Canada Limited 8023; fax (450) 433–0272; or at http://
Comply with this AD within the (Bell) Helicopters
compliance times specified, unless already
www.bellcustomer.com/files/. You may
done. AGENCY: Federal Aviation review the referenced service
(1) Remove from service the 2nd stage Administration (FAA), Department of information at the FAA, Office of the
compressor impeller at next removal of the Transportation (DOT). Regional Counsel, Southwest Region,
2nd stage compressor impeller from the 10101 Hillwood Pkwy., Room 6N–321,
ACTION: Final rule; request for
engine or before exceeding 11,500 cycles in Fort Worth, TX 76177.
service after the effective date of this AD, comments.
FOR FURTHER INFORMATION CONTACT: Rao
whichever occurs first. Edupuganti, Aviation Safety Engineer,
SUMMARY: We are adopting a new
(2) Reserved.
airworthiness directive (AD) for Bell Regulations and Policy Group,
(f) Installation Prohibition Model 427 and Model 429 helicopters. Rotorcraft Directorate, FAA, 10101
After the effective date of this AD, do not This AD requires replacing certain Hillwood Pkwy., Fort Worth, TX 76177;
install a 2nd stage compressor impeller, part engine and transmission oil check telephone (817) 222–5110; email
number (P/N) 893482–1 through –5, valves. This AD also prohibits installing rao.edupuganti@faa.gov.
asabaliauskas on DSK3SPTVN1PROD with RULES
inclusive, or P/N 3107056–1 or P/N the affected check valves on any SUPPLEMENTARY INFORMATION:
3107056–2, into any engine. helicopter. This AD is prompted by a
report of several cracked or leaking Comments Invited
(g) Alternative Methods of Compliance
(AMOCs) check valves. These actions are This AD is a final rule that involves
The Manager, Los Angeles Aircraft intended to detect and prevent a requirements affecting flight safety, and
Certification Office, FAA, may approve cracked or leaking check valve which we did not provide you with notice and
AMOCs for this AD. Use the procedures could result in loss of lubrication to the an opportunity to provide your
found in 14 CFR 39.19 to make your request. engine or transmission, failure of the comments prior to it becoming effective.
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Document Created: 2018-02-09 13:34:17
Document Modified: 2018-02-09 13:34:17
| Category | Regulatory Information | |
| Collection | Federal Register | |
| sudoc Class | AE 2.7: GS 4.107: AE 2.106: | |
| Publisher | Office of the Federal Register, National Archives and Records Administration | |
| Section | Rules and Regulations | |
| Action | Final rule. | |
| Dates | This AD is effective November 4, 2016. | |
| Contact | Joseph Costa, Aerospace Engineer, Los Angeles Aircraft Certification Office, FAA, Transport Airplane Directorate, 3960 Paramount Blvd., Lakewood, CA 90712-4137; phone: 562- 627-5246; fax: 562-627-5210; email: [email protected] | |
| FR Citation | 81 FR 67100 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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