80 FR 59672 - Airworthiness Directives; CFM International S.A. Turbofan Engines
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 80, Issue 191 (October 2, 2015)
Federal Aviation Administration
Federal Register Volume 80, Issue 191 (October 2, 2015)
| Page Range | 59672-59674 | |
| FR Document | 2015-24729 |
[Federal Register Volume 80, Number 191 (Friday, October 2, 2015)] [Proposed Rules] [Pages 59672-59674] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2015-24729] ======================================================================= ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD] RIN 2120-AA64 Airworthiness Directives; CFM International S.A. Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56-5B series turbofan engines. This proposed AD was prompted by a corrected lifing analysis by the engine manufacturer that shows the need to identify an initial and repetitive inspection threshold for certain part number (P/N) turbine rear frames (TRFs). This proposed AD would require initial and repetitive inspections of certain P/N TRFs on the low-pressure turbine (LPT) frame assembly. We are proposing this AD to prevent failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by December 1, 2015. ADDRESSES: You may send comments, using the procedures found in 14 CFR 11.43 and 11.45, by any of the following methods:Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments. Fax: 202-493-2251. Mail: U.S. Department of Transportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590. [[Page 59673]] Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this proposed AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-432-3329; email: [email protected]. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. 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- 2983; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Office (phone: 800-647-5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: [email protected]. SUPPLEMENTARY INFORMATION: Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ``Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD'' at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD because of those comments. We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this proposed AD. Discussion We were informed by CFM that it has corrected its lifing analysis for the TRF, P/N 338-102-907-0 and P/N 338-102-908-0, on the LPT frame assembly installed on CFM56-5B turbofan engines. This corrected lifing analysis shows the need for initial and repetitive inspections of certain P/N TRFs to manage low-cycle fatigue cracks. This condition, if not corrected, could result in failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. The initial and repetitive inspection intervals differ depending on whether CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0308, Revision 5, dated October 12, 2007, has been applied. We are proposing to allow engines with TRFs that have exceeded the initial inspection threshold a continued in-service allowance of 150 cycles to provide sufficient time to perform the initial inspection. The proposed repetitive inspection intervals are based on the size of the crack, if any, found during the inspection. Relevant Service Information Under 1 CFR Part 51 We reviewed CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, and CFM SB No. CFM56-5B S/B 72-0308, Revision 5, dated October 12, 2007. CFM SB No. CFM56-5B S/B 72-0850 describes procedures for inspecting the TRF. CFM SB No. CFM56-5B S/B 72-0308 identifies the engines to which this proposed AD applies. 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 of this document. FAA's Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require initial and repetitive inspections of the TRF on the LPT frame assembly. Costs of Compliance We estimate that this proposed AD would affect about 94 engines installed on airplanes of U.S. registry. We also estimate that it would take about 3 hours per engine to do the inspection. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $23,970. 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 We determined that this proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 this proposed regulation: (1) Is not a ``significant regulatory action'' under Executive Order 12866, (2) Is not a ``significant rule'' under the 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. The Proposed Amendment Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: [[Page 59674]] 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): CFM International S.A.: Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD. (a) Comments Due Date We must receive comments by December 1, 2015. (b) Affected ADs None. (c) Applicability This AD applies to CFM International S.A. (CFM) CFM56-5B engines with turbine rear frame (TRF), part number (P/N) 338-102-907-0 or P/ N 338-102-908-0, installed. (d) Unsafe Condition This AD was prompted by a corrected lifing analysis by the engine manufacturer that shows the need for an initial and repetitive inspection of certain P/N TRFs on the low-pressure turbine (LPT) frame assembly. We are issuing this AD to prevent failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For Engines that have Applied CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0308: (i) Prior to accumulating 25,000 cycles since new (CSN) on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial eddy current inspection (ECI) or a fluorescent penetrant inspection (FPI) of the TRF mount struts on the LPT assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 cycles-in-service after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, or the cumulative length of all cracks at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 1,670 cycles since last inspection (CSLI). (v) If the cumulative length of cracks at any TRF mount strut location is greater than or equal to 0.20 inches, but less than 0.25 inches, repeat the inspection within 280 CSLI. (vi) If the cumulative length of cracks at any TRF mount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (2) For Engines that have Not Applied CFM SB No. CFM56-5B S/B 72-0308: (i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial ECI or FPI of the TRF mount struts on the LPT frame assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 cycles-in-service after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, or the cumulative length of cracks at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 2,500 CSLI. (v) If the cumulative length of cracks at any TRF mount strut location is greater than or equal to 0.20 inches and less than 0.25 inches, repeat the inspection within 370 CSLI. (vi) If the cumulative length of cracks at any TRF mount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (f) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to: [email protected]. (g) Related Information (1) For more information about this AD, contact Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: [email protected]. (2) CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, and CFM SB No. CFM56-5B S/B 72-0308, Revision 5, dated October 12, 2007, can be obtained from CFM using the contact information in paragraph (g)(3) of this proposed AD. (3) For service information identified in this AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-432- 3329; email: [email protected]. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781-238-7125. Issued in Burlington, Massachusetts, on September 24, 2015. Colleen M. D'Allesandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015-24729 Filed 10-1-15; 8:45 am] BILLING CODE 4910-13-P
![59672 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Proposed Rules
■ 6. Amend § 121.103 to add paragraph shown to be extremely remote, are not (7) Determining the concern’s size. In
(a)(8) to read as follows: given present effect. determining the concern’s size, SBA
(iv) An individual, concern or other counts the receipts, employees, or the
§ 121.103 How does SBA determine entity that controls one or more other alternate size standard of the concern
affiliation? concerns cannot use options, whose size is at issue and all of its
(a) * * * convertible securities, or agreements to domestic and foreign affiliates,
(8) For SBA’s Business Loan and appear to terminate such control before regardless of whether the affiliates are
Surety Bond Guarantee programs, the actually doing so. SBA will not give organized for profit.
size standards and bases for affiliation present effect to individuals’, concerns’ (8) Exceptions to affiliation. For
are set forth in § 121.301. or other entities’ ability to divest all or exceptions to affiliation, see 13 CFR
* * * * * part of their ownership interest in order 121.103(b).
■ 7. Amend § 121.301 to add paragraph
to avoid a finding of affiliation.
Maria Contreras-Sweet,
(f) to read as follows: (3) Affiliation based on common
management. Affiliation arises where Administrator.
§ 121.301 What size standards and the CEO or President of the applicant [FR Doc. 2015–25204 Filed 10–1–15; 8:45 am]
affiliation principles are applicable to concern (or other officers, managing BILLING CODE 8025–01–P
financial assistance programs? members, or partners who control the
* * * * * management of the concern) also
(f) Concerns and entities are affiliates controls the management of one or more DEPARTMENT OF TRANSPORTATION
of each other when one controls or has other concerns. Affiliation also arises
the power to control the other, or a third where a single individual, concern or Federal Aviation Administration
party or parties controls or has the entity that controls the Board of
Directors or management of one concern 14 CFR Part 39
power to control both. It does not matter
whether control is exercised, so long as also controls the Board of Directors or [Docket No. FAA–2015–2983; Directorate
the power to control exists. For the management of one of more other Identifier 2015–NE–20–AD]
purposes of SBA’s Business Loan concerns.
(4) Affiliation based on identity of RIN 2120–AA64
Programs, Disaster Loan Program, and
Surety Bond Guarantee Program, the interest. (i) Affiliation may arise among Airworthiness Directives; CFM
following principles of affiliation apply: two or more persons (including any International S.A. Turbofan Engines
individual, concern, or other entity)
(1) Affiliation based on ownership.
with an identity of interest. An AGENCY: Federal Aviation
For determining affiliation based on
individual, concern, or entity may rebut Administration (FAA), DOT.
equity ownership, a concern is an
a determination of identity of interest ACTION: Notice of proposed rulemaking
affiliate of an individual, concern, or
with evidence showing that the interests (NPRM).
entity that owns or has the power to
deemed to be one are in fact separate.
control more than 50 percent of the (ii) SBA may presume an identity of SUMMARY: We propose to adopt a new
concern’s voting equity. If no interest between close relatives, as airworthiness directive (AD) for certain
individual, concern, or entity is found defined in 13 CFR 120.10, with identical CFM International S.A. (CFM) CFM56–
to control, SBA will deem the Board of or substantially identical business or 5B series turbofan engines. This
Directors or President or Chief economic interests (such as where the proposed AD was prompted by a
Executive Officer (CEO) (or other family members operate concerns in the corrected lifing analysis by the engine
officers, managing members, or partners same or similar industry in the same manufacturer that shows the need to
who control the management of the geographic area). identify an initial and repetitive
concern) to be in control of the concern. (5) Affiliation based on franchise and inspection threshold for certain part
(2) Affiliation arising under stock license agreements. The restraints number (P/N) turbine rear frames
options, convertible securities, and imposed on a franchisee or licensee by (TRFs). This proposed AD would
agreements to merge. (i) In determining its franchise or license agreement require initial and repetitive inspections
size, SBA considers stock options, relating to standardized quality, of certain P/N TRFs on the low-pressure
convertible securities, and agreements advertising, accounting format and other turbine (LPT) frame assembly. We are
to merge (including agreements in similar provisions, generally will not be proposing this AD to prevent failure of
principle) to have a present effect on the considered in determining whether the the TRF on the LPT frame assembly,
power to control a concern. SBA treats franchisor or licensor is affiliated with which could lead to engine separation,
such options, convertible securities, and an applicant franchisee or licensee damage to the engine, and damage to the
agreements as though the rights granted provided the applicant franchisee or airplane.
have been exercised. licensee has the right to profit from its DATES: We must receive comments on
(ii) Agreements to open or continue efforts and bears the risk of loss this proposed AD by December 1, 2015.
negotiations towards the possibility of a commensurate with ownership. ADDRESSES: You may send comments,
merger or a sale of stock at some later Affiliation may arise however, through using the procedures found in 14 CFR
date are not considered ‘‘agreements in other means, such as common 11.43 and 11.45, by any of the following
principle’’ and are thus not given ownership, common management or
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
methods:
present effect. excessive restrictions upon the sale of • Federal eRulemaking Portal: Go to
(iii) Options, convertible securities, the franchise interest. http://www.regulations.gov. Follow the
and agreements that are subject to (6) Affiliation based on SBA’s instructions for submitting comments.
conditions precedent which are determination of the totality of the • Fax: 202–493–2251.
incapable of fulfillment, speculative, circumstances. SBA may find affiliation • Mail: U.S. Department of
conjectural, or unenforceable under after considering the totality of the Transportation, Docket Operations, M–
state or Federal law, or where the circumstances, even when no single 30, West Building Ground Floor, Room
probability of the transaction (or factor is sufficient to constitute W12–140, 1200 New Jersey Avenue SE.,
exercise of the rights) occurring is affiliation. Washington, DC 20590.
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![59674 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Proposed Rules
PART 39—AIRWORTHINESS (v) If the cumulative length of cracks at any 12 New England Executive Park, Burlington,
DIRECTIVES TRF mount strut location is greater than or MA. For information on the availability of
equal to 0.20 inches, but less than 0.25 this material at the FAA, call 781–238–7125.
■ 1. The authority citation for part 39 inches, repeat the inspection within 280
Issued in Burlington, Massachusetts, on
continues to read as follows: CSLI.
September 24, 2015.
(vi) If the cumulative length of cracks at
Authority: 49 U.S.C. 106(g), 40113, 44701. any TRF mount strut location is 0.25 inches Colleen M. D’Allesandro,
or greater, replace the TRF with a part Directorate Manager, Engine & Propeller
§ 39.13 [Amended] eligible for installation before further flight. Directorate, Aircraft Certification Service.
■ 2. The FAA amends § 39.13 by adding (2) For Engines that have Not Applied CFM [FR Doc. 2015–24729 Filed 10–1–15; 8:45 am]
the following new airworthiness SB No. CFM56–5B S/B 72–0308: BILLING CODE 4910–13–P
directive (AD): (i) Prior to accumulating 32,000 CSN on
the TRF of the LPT frame assembly or within
CFM International S.A.: Docket No. FAA–
150 cycles after the effective date of this AD,
2015–2983; Directorate Identifier 2015– DEPARTMENT OF TRANSPORTATION
NE–20–AD. whichever occurs later, perform an initial ECI
or FPI of the TRF mount struts on the LPT
(a) Comments Due Date
Federal Aviation Administration
frame assembly.
We must receive comments by December 1, (ii) For engines with unknown CSN on the
TRF of the LPT frame assembly, perform the 14 CFR Part 147
2015.
initial inspection required by this AD within [Docket No. FAA–2015–3901; Notice No.
(b) Affected ADs 150 cycles-in-service after the effective date 15–10]
None. of this AD.
(iii) Use paragraph 3.B. in the RIN 2120–AK48
(c) Applicability Accomplishment Instructions of CFM SB No.
This AD applies to CFM International S.A. CFM56–5B S/B 72–0850, dated December 19, Aviation Maintenance Technician
(CFM) CFM56–5B engines with turbine rear 2012, to do the ECI and paragraph 3.C. in the Schools
frame (TRF), part number (P/N) 338–102– Accomplishment Instructions of CFM SB No.
907–0 or P/N 338–102–908–0, installed. CFM56–5B S/B 72–0850, to do the FPI. Do AGENCY: Federal Aviation
not include TRF mount strut crack lengths Administration (FAA), DOT.
(d) Unsafe Condition
towards the cumulative crack length after the ACTION: Notice of proposed rulemaking
This AD was prompted by a corrected cracks are repaired. (NPRM).
lifing analysis by the engine manufacturer (iv) If no cracks are found on any of the
that shows the need for an initial and three TRF mount struts, or the cumulative SUMMARY: The FAA proposes to amend
repetitive inspection of certain P/N TRFs on length of cracks at any TRF mount strut the regulations governing the
the low-pressure turbine (LPT) frame location is less than 0.20 inches, repeat the
assembly. We are issuing this AD to prevent
curriculum and operations of FAA-
inspection within 2,500 CSLI.
failure of the TRF on the LPT frame (v) If the cumulative length of cracks at any
certificated Aviation Maintenance
assembly, which could lead to engine TRF mount strut location is greater than or Technician Schools. These amendments
separation, damage to the engine, and equal to 0.20 inches and less than 0.25 would modernize and reorganize the
damage to the airplane. inches, repeat the inspection within 370 required curriculum subjects in the
(e) Compliance CSLI. appendices of the current regulations.
(vi) If the cumulative length of cracks at They would also remove the course
Comply with this AD within the any TRF mount strut location is 0.25 inches content items currently located in the
compliance times specified, unless already or greater, replace the TRF with a part
done.
appendices and require that they be
eligible for installation before further flight. placed in each school’s operations
(1) For Engines that have Applied CFM
Service Bulletin (SB) No. CFM56–5B S/B 72– (f) Alternative Methods of Compliance specifications so they could more easily
0308: (AMOCs) be amended when necessary. The
(i) Prior to accumulating 25,000 cycles The Manager, Engine Certification Office, amendments are needed because the
since new (CSN) on the TRF of the LPT frame FAA, may approve AMOCs for this AD. Use existing curriculums are outdated, do
assembly or within 150 cycles after the the procedures found in 14 CFR 39.19 to not meet current industry needs, and
effective date of this AD, whichever occurs make your request. You may email your can be changed only through notice and
later, perform an initial eddy current request to: ANE-AD-AMOC@faa.gov. comment rulemaking. These
inspection (ECI) or a fluorescent penetrant
inspection (FPI) of the TRF mount struts on (g) Related Information amendments would ensure that aviation
the LPT assembly. (1) For more information about this AD, maintenance technician students
(ii) For engines with unknown CSN on the contact Kyle Gustafson, Aerospace Engineer, receive up-to-date foundational training
TRF of the LPT frame assembly, perform the Engine Certification Office, FAA, Engine & to meet the demanding and consistently
initial inspection required by this AD within Propeller Directorate, 12 New England changing needs of the aviation industry.
150 cycles-in-service after the effective date Executive Park, Burlington, MA 01803; DATES: Send comments on or before
of this AD. phone: 781–238–7183; fax: 781–238–7199; December 31, 2015.
(iii) Use paragraph 3.B. in the email: kyle.gustafson@faa.gov.
Accomplishment Instructions of CFM SB No. (2) CFM SB No. CFM56–5B S/B 72–0850, ADDRESSES: Send comments identified
CFM56–5B S/B 72–0850, dated December 19, dated December 19, 2012, and CFM SB No. by docket number FAA–2015–3901
2012, to do the ECI and paragraph 3.C. in the CFM56–5B S/B 72–0308, Revision 5, dated using any of the following methods:
Accomplishment Instructions of CFM SB No. October 12, 2007, can be obtained from CFM • Federal Rulemaking Portal: Go to
asabaliauskas on DSK5VPTVN1PROD with PROPOSALS
CFM56–5B S/B 72–0850, to do the FPI. Do using the contact information in paragraph http://www.regulations.gov and follow
not include TRF mount strut crack lengths (g)(3) of this proposed AD. the online instructions for sending your
towards the cumulative crack length after the (3) For service information identified in comments electronically.
cracks are repaired. this AD, contact CFM International Inc.,
• Mail: Send comments to Docket
(iv) If no cracks are found on any of the Aviation Operations Center, 1 Neumann
three TRF mount struts, or the cumulative Way, M/D Room 285, Cincinnati, OH 45125; Operations, M–30; U.S. Department of
length of all cracks at any TRF mount strut phone: 877–432–3272; fax: 877–432–3329; Transportation (DOT), 1200 New Jersey
location is less than 0.20 inches, repeat the email: aviation.fleetsupport@ge.com. Avenue SE., Room W12–140, West
inspection within 1,670 cycles since last (4) You may view this service information Building Ground Floor, Washington, DC
inspection (CSLI). at the FAA, Engine & Propeller Directorate, 20590–0001.
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Document Created: 2015-12-15 08:44:29
Document Modified: 2015-12-15 08:44:29
| 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 | Proposed Rules | |
| Action | Notice of proposed rulemaking (NPRM). | |
| Dates | We must receive comments on this proposed AD by December 1, 2015. | |
| Contact | Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7183; fax: 781-238-7199; email: [email protected] | |
| FR Citation | 80 FR 59672 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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