81 FR 28774 - Airworthiness Directives; The Boeing Company Airplanes
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration Federal Register Volume 81, Issue 90 (May 10, 2016)
Federal Aviation Administration
Federal Register Volume 81, Issue 90 (May 10, 2016)
| Page Range | 28774-28777 | |
| FR Document | 2016-10634 |
[Federal Register Volume 81, Number 90 (Tuesday, May 10, 2016)] [Proposed Rules] [Pages 28774-28777] From the Federal Register Online [www.thefederalregister.org] [FR Doc No: 2016-10634] ----------------------------------------------------------------------- DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA-2016-6426; Directorate Identifier 2016-NM-023-AD] RIN 2120-AA64 Airworthiness Directives; The Boeing Company Airplanes AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). ----------------------------------------------------------------------- SUMMARY: We propose to adopt a new airworthiness directive (AD) for all The Boeing Company Model 737-300, -400, and -500 series airplanes. This proposed AD was prompted by reports of intergranular cracks on the front spar chord lugs of the outboard horizontal stabilizer. This proposed AD would require repetitive inspections of the front spar chord lugs and lug bores of the horizontal stabilizer, and repair if [[Page 28775]] necessary. We are proposing this AD to detect and correct cracking of the front spar chord lugs of the horizontal stabilizer. Such cracking could cause stabilizer instability, adversely affect controllability of the airplane, and adversely affect the structural integrity of the airplane. DATES: We must receive comments on this proposed AD by June 24, 2016. 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. 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 NPRM, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544-5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. It is also available on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6426. 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-2016- 6426; 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: Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; 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-2016-6426; Directorate Identifier 2016-NM-023-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 have received reports of intergranular cracks on the front spar chord lugs of the outboard horizontal stabilizer. The cracks have been found along the axis of the front spar chord and in the lug faces, lug bores, and lug spot-face surfaces. The stabilizer front spar chords are an extrusion made from 7075-T6511 aluminum. This material is susceptible to stress corrosion in a corrosive environment where residual machining stresses are present and where the material finish and sealant have degraded. A single joint failure will significantly reduce the remaining fatigue life in the rear spar. A dual failure of the upper and lower front spar joints of the horizontal stabilizer could cause stabilizer instability, adversely affect controllability of the airplane, and adversely affect the structural integrity of the airplane. Related Service Information Under 1 CFR Part 51 We reviewed Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015. The service information describes procedures for doing inspections for corrosion and cracking of the front spar chord lugs of the horizontal stabilizer, and inspections for corrosion of the lug bores. 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. 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 accomplishing the actions specified in the service information described previously, except as discussed under ``Differences Between this Proposed AD and the Service Information. For information on the procedures and compliance times, see this service information at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-6426. Differences Between This Proposed AD and the Service Information Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015, specifies to contact the manufacturer for instructions on how to repair certain conditions, but this AD would require repairing those conditions in one of the following ways: In accordance with a method that we approve; or Using data that meet the certification basis of the airplane, and that have been approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) whom we have authorized to make those findings. Costs of Compliance We estimate that this proposed AD affects 346 airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: [[Page 28776]] Estimated Costs ---------------------------------------------------------------------------------------------------------------- Cost on U.S. Action Labor cost Parts cost Cost per product operators ---------------------------------------------------------------------------------------------------------------- Inspections.................... 14 work-hours x $85 per $0 $1,190 per $411,740 per hour = $1,190 per inspection cycle. inspection cycle inspection cycle. ---------------------------------------------------------------------------------------------------------------- We have received no definitive data that would enable us to provide cost estimates for the on-condition actions specified in this proposed AD. 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, 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: 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): The Boeing Company: Docket No. FAA-2016-6426; Directorate Identifier 2016-NM-023-AD. (a) Comments Due Date We must receive comments by June 14, 2016. (b) Affected ADs None. (c) Applicability This AD applies to all The Boeing Company Model 737-300, -400, and -500 series airplanes, certificated in any category. (d) Subject Air Transport Association (ATA) of America Code 55, Stabilizers. (e) Unsafe Condition This AD was prompted by reports of intergranular cracks on the front spar chord lugs of the outboard horizontal stabilizer. We are issuing this AD to detect and correct cracking of the front spar chord lugs of the horizontal stabilizer. Such cracking could cause stabilizer instability, adversely affect controllability of the airplane, and adversely affect the structural integrity of the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Repetitive Inspections and Repairs Within 27 months after the effective date of this AD: Do the actions required by paragraphs (g)(1) and (g)(2) of this AD, and do all applicable repairs, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015, except as required by paragraph (h) of this AD. Do all applicable repairs before further flight. Repeat the inspections specified in paragraphs (g)(1) and (g)(2) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015. (1) Do a detailed inspection for corrosion and an ultrasonic inspection for cracking of the front spar chord lugs of the left and right horizontal stabilizers. (2) Do a detailed inspection for corrosion of the lug bores of the front spar chord of the left and right horizontal stabilizers. (h) Service Information Exception Where Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015, specifies to contact Boeing for appropriate action, and specifies that action as ``RC'' (Required for Compliance): Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (j) of this AD. (i) Parts Installation Limitation As of the effective date of this AD: No person may install a replacement horizontal stabilizer on any airplane, unless the actions required by paragraphs (g)(1) and (g)(2) of this AD, and all applicable repairs are done prior to installation in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015, except as required by paragraph (h) of this AD. Repeat the inspections specified in paragraph (g)(1) and (g)(2) of this AD thereafter at the applicable intervals specified in paragraph 1.E., ``Compliance,'' of Boeing Alert Service Bulletin 737-55A1092, dated August 7, 2015. (j) Alternative Methods of Compliance (AMOCs) (1) The Manager, Seattle Aircraft Certification Office (ACO), FAA, has the authority to 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 ACO, send it to the attention of the person identified in paragraph (k)(1) of this AD. Information may be emailed to: [email protected]. (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. (3) An AMOC that provides an acceptable level of safety may be used for any repair, modification, or alteration required by this AD if it is approved by the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle ACO, to make those findings. To be approved, the repair method, modification deviation, or alteration deviation must meet [[Page 28777]] the certification basis of the airplane, and the approval must specifically refer to this AD. (4) Except as required by paragraph (h) of this AD: For service information that contains steps that are labeled as RC, the provisions of paragraphs (j)(4)(i) and (j)(4)(ii) of this AD apply. (i) The steps labeled as RC, including substeps under an RC step and any figures identified in an RC step, must be done to comply with the AD. An AMOC is required for any deviations to RC steps, including substeps and identified figures. (ii) Steps not labeled as RC may be deviated from using accepted methods in accordance with the operator's maintenance or inspection program without obtaining approval of an AMOC, provided the RC steps, including substeps and identified figures, can still be done as specified, and the airplane can be put back in an airworthy condition. (k) Related Information (1) For more information about this AD, contact Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917-6577; fax: 425-917-6590; email: [email protected]. (2) For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H-65, Seattle, WA 98124-2207; telephone 206-544- 5000, extension 1; fax 206-766-5680; Internet https://www.myboeingfleet.com. You may view this referenced service information at the FAA, the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425-227-1221. Issued in Renton, Washington, on April 28, 2016. Dionne Palermo, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service. [FR Doc. 2016-10634 Filed 5-9-16; 8:45 am] BILLING CODE 4910-13-P
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(g) Replacement (j) No Alternative Actions, Intervals, or accordance with the operator’s maintenance
Within 36 months after the effective date CDCCLs or inspection program without obtaining
of this AD, do the actions required by After the maintenance or inspection approval of an AMOC, provided the RC steps,
program has been revised as required by including substeps and identified figures, can
paragraph (g)(1) or (g)(2) of this AD.
paragraph (i) of this AD, no alternative still be done as specified, and the airplane
(1) Do a replacement of the fuel pump
actions (e.g., inspections), intervals, or can be put back in an airworthy condition.
housing electrical connector with a new fuel
pump housing electrical connector, including CDCCLs may be used unless the actions, (m) Related Information
doing a general visual inspection of the intervals, or CDCCLs are approved as an
alternative method of compliance (AMOC) in (1) For more information about this AD,
protective cap for a spring and applicable contact Philip Kush, Aerospace Engineer,
accordance with the procedures specified in
replacement of the protective cap, in Propulsion Branch, ANM–140L, FAA, Los
paragraph (l) of this AD.
accordance with the Accomplishment Angeles Aircraft Certification Office (ACO),
Instructions of Boeing Service Bulletin (k) Terminating Action for Certain 3960 Paramount Boulevard, Lakewood, CA
DC10–28–264, dated May 15, 2015; or Boeing Paragraphs of Other ADs 90712–4137; phone: 562–627–5263; fax: 562–
Service Bulletin MD11–28–145, dated May Accomplishing the actions required by 627–5210; email: Philip.kush@faa.gov.
15, 2015, as applicable; and Crane Aerospace paragraph (g) of this AD terminates the (2) For The Boeing Company service
& Electronics, Hydro-Aire, Inc. Service requirements specified in paragraphs (k)(1), information identified in this AD, contact
Bulletin 60–843/845–28–2, dated October 1, (k)(2), (k)(3), and (k)(4) of this AD for that Boeing Commercial Airplanes, Attention:
2014. airplane only. Data & Services Management, 3855
(2) Do a replacement of the fuel boost (1) The actions required by paragraph (a) Lakewood Boulevard, MC D800–0019, Long
pump housing with a new fuel boost pump of AD 2000–22–21, Amendment 39–11969 Beach, CA 90846–0001; phone: 206–544–
housing, in accordance with the (65 FR 69658, dated November 20, 2000). 5000, extension 2; fax: 206–766–5683;
Accomplishment Instructions of Boeing (2) The actions required by paragraphs (a) Internet https://www.myboeingfleet.com.
Service Bulletin DC10–28–264, dated May and (b) of AD 2002–13–10, Amendment 39– (3) For Crane Aerospace & Electronics,
15, 2015; or Boeing Service Bulletin MD11– 12798 (67 FR 45053, dated July 8, 2002). Hydro-Aire, Inc. service information
28–146, dated May 15, 2015, as applicable. (3) The actions required by paragraphs (a) identified in this AD, contact Crane
and (b) of AD 2003–07–14, Amendment 39– Aerospace & Electronics, Hydro-Aire, Inc.:
(h) Repetitive Inspections 13110 (68 FR 17544, dated April 10, 2003). 3000 Winona Avenue, Burbank, CA 91510–
Within 24 months after accomplishing the (4) The actions required by paragraph (j) of 7722; phone: 818–526–2500; fax: 818–526–
replacement required by paragraph (g) of this AD 2011–11–05, Amendment 39–16704 (76 5658; email: CommSpares@
AD, do an inspection for proper operation of FR 31462, dated June 1, 2011). craneaerospace.com.
the fuel pump and all applicable corrective (4) You may view this referenced service
(l) Alternative Methods of Compliance
actions, in accordance with Appendix A, ‘‘24 information at the FAA, Transport Airplane
(AMOCs)
Month Repetitive Inspection,’’ of Boeing Directorate, 1601 Lind Avenue SW., Renton,
(1) The Manager, Los Angeles Aircraft WA. For information on the availability of
Service Bulletin DC10–28–264, dated May Certification Office (ACO), FAA, has the
15, 2015; or Boeing Service Bulletin MD11– this material at the FAA, call 425–227–1221.
authority to approve AMOCs for this AD, if
28–146, dated May 15, 2015; as applicable. requested using the procedures found in 14 Issued in Renton, WA, on April 27, 2016.
Do all applicable corrective actions before CFR 39.19. In accordance with 14 CFR 39.19, Dionne Palermo,
further flight. Repeat the inspection send your request to your principal inspector Acting Manager, Transport Airplane
thereafter at intervals not to exceed 24 or local Flight Standards District Office, as Directorate, Aircraft Certification Service.
months. appropriate. If sending information directly
[FR Doc. 2016–10735 Filed 5–9–16; 8:45 am]
to the manager of the ACO, send it to the
(i) Maintenance or Inspection Program BILLING CODE 4910–13–P
attention of the person identified in
Revision
paragraph (m)(1) of this AD. Information may
Within 30 days after accomplishing the be emailed to: 9-ANM-LAACO-AMOC-
replacement required by paragraph (g) of this Requests@faa.gov. DEPARTMENT OF TRANSPORTATION
AD, or within 30 days after the effective date (2) Before using any approved AMOC,
of this AD, whichever occurs later, revise the notify your appropriate principal inspector, Federal Aviation Administration
maintenance or inspection program, as or lacking a principal inspector, the manager
applicable, to incorporate the Critical Design of the local flight standards district office/ 14 CFR Part 39
Configuration Control Limitations (CDCCLs), certificate holding district office.
Airworthiness Limitation Instructions (ALIs), (3) An AMOC that provides an acceptable [Docket No. FAA–2016–6426; Directorate
and short-term extensions specified in level of safety may be used for any repair, Identifier 2016–NM–023–AD]
Appendices B, C, and D of Boeing Trijet modification, or alteration required by this
RIN 2120–AA64
Special Compliance Item (SCI) Report MDC– AD if it is approved by the Boeing
02K1003, Revision O, dated April 15, 2015. Commercial Airplanes Organization
Designation Authorization (ODA) that has Airworthiness Directives; The Boeing
The initial compliance time for Company Airplanes
accomplishing the actions specified in the been authorized by the Manager, Los Angeles
ACO to make those findings. To be approved, AGENCY: Federal Aviation
ALIs is at the later of the times specified in
the repair method, modification deviation, or
paragraphs (i)(1) and (i)(2) of this AD.
alteration deviation must meet the
Administration (FAA), DOT.
Revising the maintenance or inspection ACTION: Notice of proposed rulemaking
certification basis of the airplane, and the
program required by this paragraph approval must specifically refer to this AD. (NPRM).
terminates the requirements in paragraphs (g) (4) For service information that contains
and (h) of AD 2008–06–21 R1, Amendment steps that are labeled as Required for SUMMARY: We propose to adopt a new
39–16100 (74 FR 61504, November 25, 2009). Compliance (RC), the provisions of airworthiness directive (AD) for all The
(1) At the applicable time specified in paragraphs (l)(4)(i) and (l)(4)(ii) of this AD Boeing Company Model 737–300, -400,
Appendix C of Boeing Trijet SCI Report apply. and -500 series airplanes. This proposed
ehiers on DSK5VPTVN1PROD with PROPOSALS
MDC–02K1003, Revision O, dated April 15, (i) The steps labeled as RC, including AD was prompted by reports of
2015, except as provided by Appendix D of substeps under an RC step and any figures
Boeing Trijet SCI Report MDC–02K1003,
intergranular cracks on the front spar
identified in an RC step, must be done to
Revision O, dated April 15, 2015. comply with the AD. An AMOC is required
chord lugs of the outboard horizontal
(2) Within 30 days after accomplishing the for any deviations to RC steps, including stabilizer. This proposed AD would
actions required by paragraph (g) of this AD, substeps and identified figures. require repetitive inspections of the
or within 30 days after the effective date of (ii) Steps not labeled as RC may be front spar chord lugs and lug bores of
this AD, whichever occurs later. deviated from using accepted methods in the horizontal stabilizer, and repair if
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ESTIMATED COSTS
Action Labor cost Parts cost Cost per product Cost on U.S. operators
Inspections .................... 14 work-hours × $85 per hour = $1,190 per in- $0 $1,190 per inspection $411,740 per inspection
spection cycle. cycle. cycle
We have received no definitive data The Proposed Amendment ‘‘Compliance,’’ of Boeing Alert Service
that would enable us to provide cost Bulletin 737–55A1092, dated August 7, 2015.
Accordingly, under the authority (1) Do a detailed inspection for corrosion
estimates for the on-condition actions delegated to me by the Administrator,
specified in this proposed AD. and an ultrasonic inspection for cracking of
the FAA proposes to amend 14 CFR part the front spar chord lugs of the left and right
Authority for This Rulemaking 39 as follows: horizontal stabilizers.
(2) Do a detailed inspection for corrosion
Title 49 of the United States Code PART 39—AIRWORTHINESS of the lug bores of the front spar chord of the
specifies the FAA’s authority to issue DIRECTIVES left and right horizontal stabilizers.
rules on aviation safety. Subtitle I,
section 106, describes the authority of ■ 1. The authority citation for part 39 (h) Service Information Exception
the FAA Administrator. Subtitle VII: continues to read as follows: Where Boeing Alert Service Bulletin 737–
Aviation Programs, describes in more 55A1092, dated August 7, 2015, specifies to
Authority: 49 U.S.C. 106(g), 40113, 44701.
detail the scope of the Agency’s contact Boeing for appropriate action, and
authority. § 39.13 [Amended] specifies that action as ‘‘RC’’ (Required for
We are issuing this rulemaking under Compliance): Before further flight, repair
■ 2. The FAA amends § 39.13 by adding
using a method approved in accordance with
the authority described in Subtitle VII, the following new airworthiness the procedures specified in paragraph (j) of
Part A, Subpart III, Section 44701: directive (AD): this AD.
‘‘General requirements.’’ Under that The Boeing Company: Docket No. FAA–
section, Congress charges the FAA with (i) Parts Installation Limitation
2016–6426; Directorate Identifier 2016–
promoting safe flight of civil aircraft in NM–023–AD. As of the effective date of this AD: No
air commerce by prescribing regulations person may install a replacement horizontal
(a) Comments Due Date stabilizer on any airplane, unless the actions
for practices, methods, and procedures
the Administrator finds necessary for We must receive comments by June 14, required by paragraphs (g)(1) and (g)(2) of
2016. this AD, and all applicable repairs are done
safety in air commerce. This regulation
prior to installation in accordance with the
is within the scope of that authority (b) Affected ADs
Accomplishment Instructions of Boeing Alert
because it addresses an unsafe condition None. Service Bulletin 737–55A1092, dated August
that is likely to exist or develop on 7, 2015, except as required by paragraph (h)
(c) Applicability
products identified in this rulemaking of this AD. Repeat the inspections specified
action. This AD applies to all The Boeing in paragraph (g)(1) and (g)(2) of this AD
Company Model 737–300, –400, and –500 thereafter at the applicable intervals specified
Regulatory Findings series airplanes, certificated in any category. in paragraph 1.E., ‘‘Compliance,’’ of Boeing
We determined that this proposed AD (d) Subject Alert Service Bulletin 737–55A1092, dated
would not have federalism implications August 7, 2015.
Air Transport Association (ATA) of
under Executive Order 13132. This America Code 55, Stabilizers. (j) Alternative Methods of Compliance
proposed AD would not have a (AMOCs)
(e) Unsafe Condition
substantial direct effect on the States, on (1) The Manager, Seattle Aircraft
the relationship between the national This AD was prompted by reports of
intergranular cracks on the front spar chord Certification Office (ACO), FAA, has the
Government and the States, or on the authority to approve AMOCs for this AD, if
lugs of the outboard horizontal stabilizer. We
distribution of power and are issuing this AD to detect and correct requested using the procedures found in 14
responsibilities among the various cracking of the front spar chord lugs of the CFR 39.19. In accordance with 14 CFR 39.19,
levels of government. horizontal stabilizer. Such cracking could send your request to your principal inspector
For the reasons discussed above, I cause stabilizer instability, adversely affect or local Flight Standards District Office, as
certify this proposed regulation: controllability of the airplane, and adversely appropriate. If sending information directly
(1) Is not a ‘‘significant regulatory affect the structural integrity of the airplane. to the manager of the ACO, send it to the
attention of the person identified in
action’’ under Executive Order 12866, (f) Compliance paragraph (k)(1) of this AD. Information may
(2) Is not a ‘‘significant rule’’ under be emailed to: 9-ANM-Seattle-ACO-AMOC-
Comply with this AD within the
the DOT Regulatory Policies and compliance times specified, unless already Requests@faa.gov.
Procedures (44 FR 11034, February 26, done. (2) Before using any approved AMOC,
1979), notify your appropriate principal inspector,
(3) Will not affect intrastate aviation (g) Repetitive Inspections and Repairs or lacking a principal inspector, the manager
in Alaska, and Within 27 months after the effective date of the local flight standards district office/
(4) Will not have a significant of this AD: Do the actions required by certificate holding district office.
economic impact, positive or negative, paragraphs (g)(1) and (g)(2) of this AD, and (3) An AMOC that provides an acceptable
do all applicable repairs, in accordance with level of safety may be used for any repair,
ehiers on DSK5VPTVN1PROD with PROPOSALS
on a substantial number of small entities
the Accomplishment Instructions of Boeing modification, or alteration required by this
under the criteria of the Regulatory Alert Service Bulletin 737–55A1092, dated AD if it is approved by the Boeing
Flexibility Act. August 7, 2015, except as required by Commercial Airplanes Organization
List of Subjects in 14 CFR Part 39 paragraph (h) of this AD. Do all applicable Designation Authorization (ODA) that has
repairs before further flight. Repeat the been authorized by the Manager, Seattle
Air transportation, Aircraft, Aviation inspections specified in paragraphs (g)(1) and ACO, to make those findings. To be
safety, Incorporation by reference, (g)(2) of this AD thereafter at the applicable approved, the repair method, modification
Safety. intervals specified in paragraph 1.E., deviation, or alteration deviation must meet
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the certification basis of the airplane, and the P2, -1B70/75/P2, and -1B74/75/P2 SUPPLEMENTARY INFORMATION:
approval must specifically refer to this AD. turbofan engines with engine assembly,
(4) Except as required by paragraph (h) of Comments Invited
part number (P/N) 2447M10G01 or P/N
this AD: For service information that 2447M10G02, installed. This proposed We invite you to send any written
contains steps that are labeled as RC, the relevant data, views, or arguments about
provisions of paragraphs (j)(4)(i) and (j)(4)(ii)
AD was prompted by a report of a
significant fan rub event. This proposed this NPRM. Send your comments to an
of this AD apply.
(i) The steps labeled as RC, including AD would require rework of the engine address listed under the ADDRESSES
substeps under an RC step and any figures fan stator module assembly. We are section. Include ‘‘Docket No. FAA–
identified in an RC step, must be done to proposing this AD to prevent failure of 2016–5872; Directorate Identifier 2016–
comply with the AD. An AMOC is required the fan blades and the load reduction NE–11–AD’’ at the beginning of your
for any deviations to RC steps, including device, loss of power to one or more comments. We specifically invite
substeps and identified figures. engines, loss of thrust control, and loss comments on the overall regulatory,
(ii) Steps not labeled as RC may be of the airplane. economic, environmental, and energy
deviated from using accepted methods in aspects of this NPRM. We will consider
DATES: We must receive comments on
accordance with the operator’s maintenance
this proposed AD by July 11, 2016. all comments received by the closing
or inspection program without obtaining
approval of an AMOC, provided the RC steps, ADDRESSES: You may send comments, date and may amend this NPRM
including substeps and identified figures, can using the procedures found in 14 CFR because of those comments.
still be done as specified, and the airplane 11.43 and 11.45, by any of the following We will post all comments we
can be put back in an airworthy condition. methods: receive, without change, to http://
• Federal eRulemaking Portal: Go to www.regulations.gov, including any
(k) Related Information
http://www.regulations.gov. Follow the personal information you provide. We
(1) For more information about this AD, will also post a report summarizing each
contact Gaetano Settineri, Aerospace
instructions for submitting comments.
Engineer, Airframe Branch, ANM–120S,
• Fax: 202–493–2251. substantive verbal contact we receive
FAA, Seattle Aircraft Certification Office • Mail: U.S. Department of about this NPRM.
(ACO), 1601 Lind Avenue SW., Renton, WA Transportation, Docket Operations, M– Discussion
98057–3356; phone: 425–917–6577; fax: 425– 30, West Building Ground Floor, Room
917–6590; email: gaetano.settineri@faa.gov. W12–140, 1200 New Jersey Avenue SE., We received a report of a significant
(2) For service information identified in Washington, DC 20590. fan rub event involving a GE GEnx-1B
this AD, contact Boeing Commercial • Hand Delivery: Deliver to Mail Performance Improvement Program 2
Airplanes, Attention: Data & Services address above between 9 a.m. and 5 (PIP2) engine. The fan rub was caused
Management, P.O. Box 3707, MC 2H–65, p.m., Monday through Friday, except by partial fan ice shedding. Asymmetric
Seattle, WA 98124–2207; telephone 206– Federal holidays. ice shedding can cause large fan
544–5000, extension 1; fax 206–766–5680; For service information identified in imbalances leading to heavy tip rubs.
Internet https://www.myboeingfleet.com. You this NPRM, contact General Electric The fan case geometry on PIP2 engines
may view this referenced service information
at the FAA, the FAA, Transport Airplane
Company, GE Aviation, Room 285, 1 makes these engines susceptible to
Directorate, 1601 Lind Avenue SW., Renton, Neumann Way, Cincinnati, OH 45215; heavy fan tip rubs. This can cause
WA. For information on the availability of phone: 513–552–3272; email: substantial damage to the engine and an
this material at the FAA, call 425–227–1221. aviation.fleetsupport@ge.com. You may in-flight non-restartable power loss. We
Issued in Renton, Washington, on April 28, view this service information at the are using calendar time for compliance
2016. FAA, Engine & Propeller Directorate, in this AD because the failure mode is
Dionne Palermo, 1200 District Avenue, Burlington, MA caused by exposure to specific
Acting Manager, Transport Airplane
01803. For information on the environmental and operational
Directorate, Aircraft Certification Service. availability of this material at the FAA, conditions. This defines the overall fleet
call 781–238–7125. risk in terms of calendar time, rather
[FR Doc. 2016–10634 Filed 5–9–16; 8:45 am]
Examining the AD Docket than engine cycles or hours.
BILLING CODE 4910–13–P
This condition, if not corrected, could
You may examine the AD docket on result in failure of the fan blades and the
the Internet at http:// load reduction device, loss of power to
DEPARTMENT OF TRANSPORTATION www.regulations.gov by searching for one or more engines, loss of thrust
and locating Docket No. FAA–2016– control, and loss of the airplane.
Federal Aviation Administration 5872; or in person at the Docket
Management Facility between 9 a.m. Related Service Information Under 1
14 CFR Part 39 and 5 p.m., Monday through Friday, CFR Part 51
[Docket No. FAA–2016–5872; Directorate except Federal holidays. The AD docket We reviewed GE GEnx–1B Service
Identifier 2016–NE–11–AD] contains this proposed AD, the Bulletin (SB) 72–0314 R00, dated April
regulatory evaluation, any comments 1, 2016. The SB describes procedures
RIN 2120–AA64 received, and other information. The for increasing the clearance of the fan
street address for the Docket Office stator module assembly. This service
Airworthiness Directives; General
(phone: 800–647–5527) is in the information is reasonably available
Electric Company Turbofan Engines
ADDRESSES section. Comments will be because the interested parties have
AGENCY: Federal Aviation available in the AD docket shortly after access to it through their normal course
receipt.
ehiers on DSK5VPTVN1PROD with PROPOSALS
Administration (FAA), DOT. of business or by the means identified
ACTION: Notice of proposed rulemaking FOR FURTHER INFORMATION CONTACT: in the ADDRESSES section.
(NPRM). Christopher McGuire, Aerospace
Engineer, Engine Certification Office, FAA’s Determination
SUMMARY: We propose to adopt a new FAA, Engine & Propeller Directorate, We are proposing this NPRM because
airworthiness directive (AD) for all 1200 District Avenue, Burlington, MA we evaluated all the relevant
General Electric Company (GE) GEnx- 01803; phone: 781–238–7120; fax: 781– information and determined the unsafe
1B64/P2, -1B67/P2, -1B70/P2, -1B70C/ 238–7199; email: chris.mcguire@faa.gov. condition described previously is likely
VerDate Sep<11>2014 15:20 May 09, 2016 Jkt 238001 PO 00000 Frm 00042 Fmt 4702 Sfmt 4702 E:\FR\FM\10MYP1.SGM 10MYP1](https://thefederalregister.org/doc/81_FR_28864/page/4.svg)
Document Created: 2016-05-10 05:18:36
Document Modified: 2016-05-10 05:18:36
| 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 June 24, 2016. | |
| Contact | Gaetano Settineri, Aerospace Engineer, Airframe Branch, ANM-120S, FAA, Seattle Aircraft Certification Office (ACO), 1601 Lind Avenue SW., Renton, WA 98057-3356; phone: 425-917- 6577; fax: 425-917-6590; email: [email protected] | |
| FR Citation | 81 FR 28774 | |
| RIN Number | 2120-AA64 | |
| CFR Associated | Air Transportation; Aircraft; Aviation Safety; Incorporation by Reference and Safety |
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