81 FR 19022 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration

Federal Register Volume 81, Issue 64 (April 4, 2016)

Page Range		19022-19024
FR Document		2016-07377

We are adopting a new airworthiness directive (AD) for all General Electric Company (GE) CF6-80E1 turbofan engines with rotating compressor discharge pressure (CDP) seal, part number (P/N) 1669M73P02, installed. This AD was prompted by reports from the manufacturer of cracks in the teeth of two rotating CDP seals found during engine shop visits. This AD requires stripping of the coating, inspecting, and recoating the teeth of the affected rotating CDP seals. We are issuing this AD to prevent cracking of the CDP seal teeth, uncontained part release, damage to the engine, and damage to the airplane.

Federal Register, Volume 81 Issue 64 (Monday, April 4, 2016)

[Federal Register Volume 81, Number 64 (Monday, April 4, 2016)]
[Rules and Regulations]
[Pages 19022-19024]
From the Federal Register Online  [www.thefederalregister.org]
[FR Doc No: 2016-07377]


=======================================================================
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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4023; Directorate Identifier 2015-NE-29-AD; 
Amendment 39-18445; AD 2016-06-14]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for all 
General Electric Company (GE) CF6-80E1 turbofan engines with rotating 
compressor discharge pressure (CDP) seal, part number (P/N) 1669M73P02, 
installed. This AD was prompted by reports from the manufacturer of 
cracks in the teeth of two rotating CDP seals found during engine shop 
visits. This AD requires stripping of the coating, inspecting, and 
recoating the teeth of the affected rotating CDP seals. We are issuing 
this AD to prevent cracking of the CDP seal teeth, uncontained part 
release, damage to the engine, and damage to the airplane.

DATES: This AD is effective May 9, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 9, 2016.

ADDRESSES: For service information identified in this final rule, 
contact General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected]. You may view this service information at 
the FAA, Engine & Propeller Directorate, 1200 District Avenue, 
Burlington, MA. For information on the availability of this material at 
the FAA, call 781-238-7125. It is also available on the Internet at 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2015-4023.

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-
4023; 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: Herman Mak, Aerospace Engineer, Engine 
Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7147; fax: 781-
238-7199; 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 all GE CF6-80E1 turbofan 
engines with rotating CDP seal, P/N 1669M73P02, installed. The NPRM 
published in the Federal Register on November 17, 2015 (80 FR 71747). 
The NPRM was prompted by reports of cracks in the teeth of two rotating 
CDP seals found during engine shop visits. The NPRM proposed to require 
stripping of the coating, inspecting, and recoating the teeth of the 
affected rotating CDP seals. We are issuing this AD to prevent cracking 
of the CDP seal teeth, 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 (80 
FR 71747, November 17, 2015) (``the NPRM'') and the FAA's response to 
each comment.

Request To Clarify Definition

    Qantas, Air France, KLM Royal Dutch Airlines (KLM), and GE Aviation 
requested that the shop visit definition be clarified to allow for 
randomly occurring exemptions. Including exemptions would not increase 
the time between full shop visits.
    We agree. We changed the shop visit definition to include specific 
conditions that do not qualify as shop visits.

Request To Clarify the Shop Visit Definition

    KLM and Air France requested we clarify the phrase ``separation of 
pairs of major mating engine flanges''.
    We agree. We changed the definition for engine shop visit.

Request To Change Compliance Time

    Qantas requested a more restrictive compliance time for engines 
that experience blade-out events and a less restrictive compliance time 
of next part

[[Page 19023]]

exposure for all other affected engines. Only engines that experience 
blade-out conditions require urgent compliance times.
    We disagree. The compliance times in the NPRM were derived from 
analysis that includes the risks associated with engines with and 
without blade-out events. We did not change this AD.

Request To Clarify Compliance

    Qantas requested that we clarify the specific type of stationary 
CDP seal repair and that we clarify what is considered a replaced 
stationary CDP seal.
    We agree. We modified the Compliance section to specify the repair 
as `honeycomb'. We also added a definition to define a replaced CDP 
seal.

Request To Change Applicability

    KLM requested that the applicability be expanded to include spare 
parts.
    We partially agree. We agree with the concern for accidental 
installation of borazon-nickel coated rotating CDP seals because the 
NPRM does not preclude this scenario. We disagree with expanding this 
AD to include spare parts because ADs address unsafe conditions of 
engines, not spare parts. We changed this AD by adding an installation 
prohibition paragraph to address this concern.

Request To Change Credit for Previous Action

    KLM requested the Credit for Previous Action paragraph allow for 
other approved original equipment manufacturer approved procedures for 
stripping and recoating rotating CDP seal teeth. KLM recoated two CDP 
seals using a procedure approved by GE.
    We disagree. It is unknown whether previous recoating procedures 
are equivalent to the procedures specified in the Credit for Previous 
Action paragraph of this AD. Any party may submit a request for an 
Alternative Method of Compliance using the procedures listed in this 
AD. We did not change this AD.

Additional Changes

    We clarified paragraphs (e)(2)(i) and (e)(2)(ii) of this AD.
    We updated the cost estimate. We changed the Costs of Compliance 
paragraph of this AD by increasing the number of affected engines by 
four and updating the costs accordingly.

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 Under 1 CFR Part 51

    We reviewed GE Service Bulletin (SB) CF6-80E1 S/B 72-0529, Revision 
01, dated August 21, 2015. The SB describes procedures for stripping, 
inspecting, and replacing the seal tooth coating on the affected 
rotating CDP seals. 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 GE CF6-80E1 (GEK99376) Engine Manual, Revision 42, 
dated March 15, 2014. The engine manual describes acceptable repair 
procedures for the seal teeth.

Costs of Compliance

    We estimate that this AD will affect 10 engines installed on 
airplanes of U.S. registry. We also estimate that it will take about 
7.15 hours per engine to comply with this AD. The average labor rate is 
$85 per hour. Parts would cost about $7,835 per engine. Based on these 
figures, we estimate the total cost of this AD to U.S. operators to be 
$84,428.

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:

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):

2016-06-14 General Electric Company: Amendment 39-18445; Docket No. 
FAA-2015-4023; Directorate Identifier 2015-NE-29-AD.

(a) Effective Date

    This AD is effective May 9, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all General Electric Company (GE) CF6-80E1 
turbofan engines with rotating compressor discharge pressure (CDP) 
seals, part number (P/N) 1669M73P02, installed.

(d) Unsafe Condition

    This AD was prompted by reports from the manufacturer of cracks 
in the teeth of two rotating CDP seals found during engine shop 
visits. We are issuing this AD to prevent cracking of the CDP seal 
teeth, which can lead to uncontained part release, damage to the 
engine, and damage to the airplane.

(e) Compliance

    (1) Comply with this AD within the compliance times specified, 
unless already done.

[[Page 19024]]

    (2) Strip coating, inspect, and recoat the teeth of the rotating 
CDP seal, P/N 1669M73P02. Use paragraph 3.C.(2) of GE Service 
Bulletin (SB) CF6-80E1 S/B 72-0529, Revision 01, dated August 21, 
2015 to do the strip coating, inspecting, and recoating, as follows:
    (i) For engines that have had stationary CDP seal, P/N 
1347M28G02, replaced or stationary CDP seal honeycomb repaired; 
strip coating, inspect, and recoat the teeth of the rotating CDP 
seal at the next engine shop visit.
    (ii) For engines that have not had stationary CDP seal, P/N 
1347M28G02, replaced or stationary CDP seal honeycomb repaired; 
strip coating, inspect, and recoat the teeth of the rotating CDP 
seal at the next part exposure of the rotating CDP seal.

(f) Installation Prohibition

    After the effective date of this AD, do not install any rotating 
CDP seal, P/N 1669M73P02, that has not had its seal teeth recoated 
using procedures specified in ESM 72-31-10, REPAIR 002 of GE CF6-
80E1 (GEK99376) Engine Manual, Revision 42, dated March 15, 2014, 
into any engine.

(g) Definitions

    (1) For the purpose of this AD, exposure of the rotating CDP 
seal is defined as removal of the compressor rear frame from the 
high-pressure compressor (HPC) module.
    (2) For the purpose of this AD, an engine shop visit is defined 
as the induction of an engine into the shop for maintenance 
involving the separation of any major mating engine flanges, except 
that the separation of engine flanges solely for the following 
purposes is not considered a shop visit:
    (i) Transportation without subsequent engine maintenance.
    (ii) Removing the turbine rear frame (TRF) for repair of TRF 
cracking.
    (iii) Removing the top or bottom HPC case, or both, for HPC 
airfoil maintenance.
    (iv) Removing only the accessory gearbox and/or transfer 
gearbox.
    (v) Replacing the high-pressure turbine (HPT) stage 1 blades per 
CF6-80E1 SB 72-0504 ``Quick-Turn Workscope Procedure to Replace CF6-
80E1 Stage 1 HPT Blades''.
    (3) For the purpose of this AD, a stationary CDP seal is 
replaced if at any previous shop visit, the seal has been removed 
and a different seal is installed.

(h) Credit for Previous Action

    You may take credit for the actions that are required by 
paragraph (e) of this AD if the actions were performed before the 
effective date of this AD using the procedures in ESM 72-31-10, 
REPAIR 002 of the GE CF6-80E1 (GEK99376) Engine Manual, Revision 42, 
dated March 15, 2014, or earlier versions.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request. You may email your request to: [email protected].

(j) Related Information

    (1) For more information about this AD, contact Herman Mak, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7147; fax: 781-238-7199; email: [email protected].

(k) 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.
    (i) General Electric Company Service Bulletin CF6-80E1 S/B 72-
0529, Revision 01, dated August 21, 2015.
    (ii) Reserved.
    (3) For GE service information identified in this AD, contact 
General Electric Company, GE Aviation, Room 285, 1 Neumann Way, 
Cincinnati, OH 45215; phone: 513-552-3272; email: 
[email protected].
    (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.
    (5) You may view this service information 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 March 16, 2016.
Ann C. Mollica,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-07377 Filed 4-1-16; 8:45 am]
 BILLING CODE 4910-13-P

19022 Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations

of 1982, secs. 117(a), 132, 133, 134, 135, 137, DEPARTMENT OF TRANSPORTATION Document Management Facility, U.S.
141, 145(g), 148, 218(a) (42 U.S.C. 10137(a), Department of Transportation, Docket
10152, 10153, 10154, 10155, 10157, 10161, Federal Aviation Administration Operations, M–30, West Building
10165(g), 10168, 10198(a)); 44 U.S.C. 3504 Ground Floor, Room W12–140, 1200
note. 14 CFR Part 39 New Jersey Avenue SE., Washington,
■ 2. In § 72.214, Certificate of [Docket No. FAA–2015–4023; Directorate DC 20590.
Compliance No. 1014 is revised to read Identifier 2015–NE–29–AD; Amendment 39– FOR FURTHER INFORMATION CONTACT:
as follows: 18445; AD 2016–06–14] Herman Mak, Aerospace Engineer,
Engine Certification Office, FAA, Engine
§ 72.214 List of approved spent fuel RIN 2120–AA64
& Propeller Directorate, 1200 District
storage casks. Avenue, Burlington, MA 01803; phone:
Airworthiness Directives; General
* * * * * 781–238–7147; fax: 781–238–7199;
Electric Company Turbofan Engines
Certificate Number: 1014. email: herman.mak@faa.gov.
AGENCY: Federal Aviation SUPPLEMENTARY INFORMATION:
Initial Certificate Effective Date: May Administration (FAA), DOT.
31, 2000. Discussion
ACTION: Final rule.
Amendment Number 1 Effective Date: We issued a notice of proposed
July 15, 2002. SUMMARY: We are adopting a new rulemaking (NPRM) to amend 14 CFR
Amendment Number 2 Effective Date: airworthiness directive (AD) for all part 39 by adding an AD that would
June 7, 2005. General Electric Company (GE) CF6– apply to all GE CF6–80E1 turbofan
80E1 turbofan engines with rotating engines with rotating CDP seal, P/N
Amendment Number 3 Effective Date: compressor discharge pressure (CDP)
May 29, 2007. 1669M73P02, installed. The NPRM
seal, part number (P/N) 1669M73P02, published in the Federal Register on
Amendment Number 4 Effective Date: installed. This AD was prompted by November 17, 2015 (80 FR 71747). The
January 8, 2008. reports from the manufacturer of cracks NPRM was prompted by reports of
Amendment Number 5 Effective Date: in the teeth of two rotating CDP seals cracks in the teeth of two rotating CDP
July 14, 2008. found during engine shop visits. This seals found during engine shop visits.
AD requires stripping of the coating, The NPRM proposed to require
Amendment Number 6 Effective Date:
inspecting, and recoating the teeth of stripping of the coating, inspecting, and
August 17, 2009.
the affected rotating CDP seals. We are recoating the teeth of the affected
Amendment Number 7 Effective Date: issuing this AD to prevent cracking of rotating CDP seals. We are issuing this
December 28, 2009. the CDP seal teeth, uncontained part AD to prevent cracking of the CDP seal
Amendment Number 8 Effective Date: release, damage to the engine, and teeth, uncontained part release, damage
May 2, 2012, as corrected on November damage to the airplane. to the engine, and damage to the
16, 2012 (ADAMS Accession No. DATES: This AD is effective May 9, 2016. airplane.
ML12213A170); superseded by The Director of the Federal Register
Comments
Amendment Number 8, Revision 1, on approved the incorporation by reference
February 16, 2016. of a certain publication listed in this AD We gave the public the opportunity to
as of May 9, 2016. participate in developing this AD. The
Amendment Number 8, Revision 1,
ADDRESSES: For service information
following presents the comments
Effective Date: February 16, 2016.
identified in this final rule, contact received on the NPRM (80 FR 71747,
Amendment Number 9 Effective Date: November 17, 2015) (‘‘the NPRM’’) and
March 11, 2014, superseded by General Electric Company, GE Aviation,
Room 285, 1 Neumann Way, Cincinnati, the FAA’s response to each comment.
Amendment Number 9, Revision 1, on
March 21, 2016. OH 45215; phone: 513–552–3272; email: Request To Clarify Definition
aviation.fleetsupport@ge.com. You may Qantas, Air France, KLM Royal Dutch
Amendment Number 9, Revision 1, view this service information at the
Effective Date: March 21, 2016. Airlines (KLM), and GE Aviation
FAA, Engine & Propeller Directorate, requested that the shop visit definition
Safety Analysis Report (SAR) 1200 District Avenue, Burlington, MA. be clarified to allow for randomly
Submitted by: Holtec International. For information on the availability of occurring exemptions. Including
SAR Title: Final Safety Analysis this material at the FAA, call 781–238– exemptions would not increase the time
Report for the HI–STORM 100 Cask 7125. It is also available on the Internet between full shop visits.
System. at http://www.regulations.gov by We agree. We changed the shop visit
searching for and locating Docket No. definition to include specific conditions
Docket Number: 72–1014. FAA–2015–4023. that do not qualify as shop visits.
Certificate Expiration Date: May 31,
2020. Examining the AD Docket Request To Clarify the Shop Visit
Model Number: HI–STORM 100. You may examine the AD docket on Definition
the Internet at http:// KLM and Air France requested we
* * * * *
www.regulations.gov by searching for clarify the phrase ‘‘separation of pairs of
Dated at Rockville, Maryland, this 30th day and locating Docket No. FAA–2015– major mating engine flanges’’.
of March, 2016. 4023; or in person at the Docket We agree. We changed the definition
mstockstill on DSK4VPTVN1PROD with RULES

For the Nuclear Regulatory Commission. Management Facility between 9 a.m. for engine shop visit.
Cindy Bladey, and 5 p.m., Monday through Friday,
Chief, Rules, Announcements, and Directives except Federal holidays. The AD docket Request To Change Compliance Time
Branch, Division of Administrative Services, contains this AD, the regulatory Qantas requested a more restrictive
Office of Administration. evaluation, any comments received, and compliance time for engines that
[FR Doc. 2016–07618 Filed 4–1–16; 8:45 am] other information. The address for the experience blade-out events and a less
BILLING CODE 7590–01–P Docket Office (phone: 800–647–5527) is restrictive compliance time of next part

VerDate Sep<11>2014 17:02 Apr 01, 2016 Jkt 238001 PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 E:\FR\FM\04APR1.SGM 04APR1

Federal Register / Vol. 81, No. 64 / Monday, April 4, 2016 / Rules and Regulations 19023

exposure for all other affected engines. We also determined that these government and the States, or on the
Only engines that experience blade-out changes will not increase the economic distribution of power and
conditions require urgent compliance burden on any operator or increase the responsibilities among the various
times. scope of this AD. levels of government.
We disagree. The compliance times in For the reasons discussed above, I
the NPRM were derived from analysis Related Service Information Under 1 certify that this AD:
that includes the risks associated with CFR Part 51 (1) Is not a ‘‘significant regulatory
engines with and without blade-out We reviewed GE Service Bulletin (SB) action’’ under Executive Order 12866,
events. We did not change this AD. CF6–80E1 S/B 72–0529, Revision 01, (2) Is not a ‘‘significant rule’’ under
dated August 21, 2015. The SB DOT Regulatory Policies and Procedures
Request To Clarify Compliance (44 FR 11034, February 26, 1979),
describes procedures for stripping,
Qantas requested that we clarify the inspecting, and replacing the seal tooth (3) Will not affect intrastate aviation
specific type of stationary CDP seal coating on the affected rotating CDP in Alaska to the extent that it justifies
repair and that we clarify what is seals. This service information is making a regulatory distinction, and
considered a replaced stationary CDP reasonably available because the (4) Will not have a significant
seal. interested parties have access to it economic impact, positive or negative,
We agree. We modified the through their normal course of business on a substantial number of small entities
Compliance section to specify the repair or by the means identified in the under the criteria of the Regulatory
as ‘honeycomb’. We also added a ADDRESSES section. Flexibility Act.
definition to define a replaced CDP seal.
Other Related Service Information List of Subjects in 14 CFR Part 39
Request To Change Applicability Air transportation, Aircraft, Aviation
We reviewed GE CF6–80E1
KLM requested that the applicability (GEK99376) Engine Manual, Revision safety, Incorporation by reference,
be expanded to include spare parts. 42, dated March 15, 2014. The engine Safety.
We partially agree. We agree with the
manual describes acceptable repair Adoption of the Amendment
concern for accidental installation of
procedures for the seal teeth.
borazon-nickel coated rotating CDP Accordingly, under the authority
seals because the NPRM does not Costs of Compliance delegated to me by the Administrator,
preclude this scenario. We disagree with We estimate that this AD will affect the FAA amends 14 CFR part 39 as
expanding this AD to include spare 10 engines installed on airplanes of U.S. follows:
parts because ADs address unsafe registry. We also estimate that it will
conditions of engines, not spare parts. PART 39—AIRWORTHINESS
take about 7.15 hours per engine to DIRECTIVES
We changed this AD by adding an comply with this AD. The average labor
installation prohibition paragraph to rate is $85 per hour. Parts would cost
address this concern. ■ 1. The authority citation for part 39
about $7,835 per engine. Based on these continues to read as follows:
Request To Change Credit for Previous figures, we estimate the total cost of this Authority: 49 U.S.C. 106(g), 40113, 44701.
Action AD to U.S. operators to be $84,428.
KLM requested the Credit for Previous § 39.13 [Amended]
Authority for This Rulemaking
Action paragraph allow for other ■ 2. The FAA amends § 39.13 by adding
Title 49 of the United States Code
approved original equipment the following new airworthiness
specifies the FAA’s authority to issue
manufacturer approved procedures for directive (AD):
rules on aviation safety. Subtitle I,
stripping and recoating rotating CDP 2016–06–14 General Electric Company:
seal teeth. KLM recoated two CDP seals section 106, describes the authority of
the FAA Administrator. Subtitle VII: Amendment 39–18445; Docket No.
using a procedure approved by GE. FAA–2015–4023; Directorate Identifier
We disagree. It is unknown whether Aviation Programs, describes in more 2015–NE–29–AD.
previous recoating procedures are detail the scope of the Agency’s
authority. (a) Effective Date
equivalent to the procedures specified
in the Credit for Previous Action We are issuing this rulemaking under This AD is effective May 9, 2016.
paragraph of this AD. Any party may the authority described in Subtitle VII, (b) Affected ADs
submit a request for an Alternative Part A, Subpart III, Section 44701:
None.
Method of Compliance using the ‘‘General requirements.’’ Under that
procedures listed in this AD. We did not section, Congress charges the FAA with (c) Applicability
change this AD. promoting safe flight of civil aircraft in This AD applies to all General Electric
air commerce by prescribing regulations Company (GE) CF6–80E1 turbofan engines
Additional Changes for practices, methods, and procedures with rotating compressor discharge pressure
We clarified paragraphs (e)(2)(i) and the Administrator finds necessary for (CDP) seals, part number (P/N) 1669M73P02,
safety in air commerce. This regulation installed.
(e)(2)(ii) of this AD.
We updated the cost estimate. We is within the scope of that authority (d) Unsafe Condition
changed the Costs of Compliance because it addresses an unsafe condition This AD was prompted by reports from the
paragraph of this AD by increasing the that is likely to exist or develop on manufacturer of cracks in the teeth of two
number of affected engines by four and products identified in this rulemaking rotating CDP seals found during engine shop
updating the costs accordingly. action. visits. We are issuing this AD to prevent
mstockstill on DSK4VPTVN1PROD with RULES

cracking of the CDP seal teeth, which can
Conclusion Regulatory Findings lead to uncontained part release, damage to
We reviewed the relevant data, This AD will not have federalism the engine, and damage to the airplane.
considered the comments received, and implications under Executive Order (e) Compliance
determined that air safety and the 13132. This AD will not have a (1) Comply with this AD within the
public interest require adopting this AD substantial direct effect on the States, on compliance times specified, unless already
with the changes described previously. the relationship between the national done.

VerDate Sep<11>2014 17:02 Apr 01, 2016 Jkt 238001 PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 E:\FR\FM\04APR1.SGM 04APR1

Document Created: 2016-04-02 03:54:07
Document Modified: 2016-04-02 03:54:07

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 May 9, 2016.
Contact		Herman Mak, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781-238-7147; fax: 781- 238-7199; email: [email protected]
FR Citation		81 FR 19022
RIN Number		2120-AA64
CFR Associated		Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety

81 FR 19022 - Airworthiness Directives; General Electric Company Turbofan Engines

DEPARTMENT OF TRANSPORTATIONFederal Aviation Administration

Federal Register Volume 81, Issue 64 (April 4, 2016)

DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration