### 57536 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules

this AD at whichever of the following occurs later:

(i) The v-band coupling reaches a total of 1,000 hours time-in-service (TIS); or

(ii) 50 hours TIS after the effective date of this AD, or 6 months after the effective date of this AD, whichever occurs earlier.

(2) After the initial replacement required in paragraph (j)(1) of this AD, repetitively thereafter replace the v-band coupling every 1,000 hours TIS.
(k) Flange and V-Band Coupling

(1) Install serviceable and replacement vband couplings following the applicable instructions contained in Piper Aircraft Corporation Service Bulletin No. 644E, dated May 9, 2012 and/or Lycoming Service Instruction No. 1238B, dated January 6, 2010.

(2) Use the applicable torque values specified within Piper Aircraft Corporation Service Bulletin No. 644E, dated May 9, 2012, for Piper v-band couplings; and within Lycoming Service Instruction No. 1238B, dated January 6, 2010, for Lycoming v-band couplings; making sure the torque indicator wrench socket is properly aligned to prevent side loads upon the (v-band coupling) bolt.

(3) Align each flange couple so that mating flange surfaces are flat against each other (do not use a v-band coupling to pull flanges into alignment).

(4) Verify that the locknuts exhibit a prevailing torque, and replace any locknuts and/or mating couplings with airworthy parts when locknuts are not exhibiting a prevailing torque.

Note 1 to paragraph (k) of this AD: During installation, we recommend not opening the v-band coupling more than the MINIMUM diameter necessary to clear coupled flanges.

(l) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Atlanta 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 the Related Information section of this AD.

(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.

(m) Related Information

(1) For more information about this AD, contact Gary Wechsler, Aerospace Engineer, Atlanta ACO, FAA, 1701 Columbia Avenue, College Park, Georgia 30337; telephone: (404) 474–5575; fax: (404) 474–5606; email: gary.wechsler@faa.gov.

(2) For service information identified in this AD, contact Piper Aircraft, Inc., 2926 Piper Drive, Vero Beach, Florida 32960; telephone: (772) 567–4361; fax: (772) 978– 6573; Internet: www.piper.com/home/pages/ Publications.cfm. You may review copies of the referenced service information at the FAA, Small Airplane Directorate, 901 Locust, Kansas City, Missouri 64106. For information on the availability of this material at the FAA, call (816) 329–4148.

Issued in Kansas City, Missouri, on September 11, 2012. Earl Lawrence, Manager, Small Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–22953 Filed 9–17–12; 8:45 am]

**BILLING CODE 4910–13–P**

**DEPARTMENT OF TRANSPORTATION**

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0936; Directorate Identifier 2011–NM–269–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 certain The Boeing Company Model 737–700 and –700C series airplanes. This proposed AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. This proposed AD would require repetitive inspections for cracking of the fuselage skin at certain locations at chem-mill areas, and repair if necessary. We are proposing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.

**DATES :**  We must receive comments on this proposed AD by November 2, 2012.

**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 proposed 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 review copies of the referenced service information at the FAA, Transport Airplane Directorate; 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call 425–227–1221. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; 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 :**  Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6447; fax: (425) 917–6590; email: Wayne.Lockett@faa.gov

. **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– 2012–0936; Directorate Identifier 2011– NM–269–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 received reports of early fatigue cracks near chem-mill areas on the crown skin panels of Model 737–300, –400, and –500 series airplanes. The cracks resulted from high stresses in the areas where chem-mill pockets are adjacent to non-chem-mill areas.


### 57537 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules

Although we have not received any reports of this type of fuselage fatigue cracks on Model 737–600, –700, –700C, –800, –900, or –900ER series airplanes, a full-scale fatigue test article was inspected for skin cracks at similar structural details and two chem-mill cracks were found that occurred late in the testing program. This condition, if not detected and corrected, could result in rapid decompression of the airplane.

Relevant Service Information

We reviewed Boeing Service Bulletin 737–53–1310, dated October 20, 2011, for Model 737–700 and –700C series airplanes. That service bulletin describes, among other things, procedures for doing repetitive externaldetailed inspections and external nondestructive inspections (medium frequency eddy current (MFEC), magneto optic imager (MOI), C-scan, or ultrasonic phased array (UTPA) inspections) of the fuselage skin at specified locations where chem-mill areas are adjacent to non-chem-mill areas at antenna and door bearstrap installations, and repairs if necessary.

Boeing Service Bulletin 737–53–1310, dated October 20, 2011, also describes procedures for installing modification doublers, which involves an externaldetailed inspection and an external nondestructive (MFEC, MOI, C-scan, or UTPA) inspection for any cracking of the area to be modified prior to the doubler being placed on that area, a high frequency eddy current inspection of all existing holes for cracking, and contacting Boeing if necessary. That service bulletin also specifies that when a modification is accomplished, the repetitive inspection for the area under the modification is no longer necessary.

Boeing Service Bulletin 737–53–1310, dated October 20, 2011, specifies an initial compliance time of 43,000 total flight cycles, or 1,500 flight cycles after the original issue date of that service bulletin, whichever occurs later. That service bulletin specifies a repetitive interval not to exceed 1,500 flight cycles or 2,100 flight cycles, depending on inspection method.

For airplanes that have incorporated Boeing Business Jet (BBJ) lower cabin altitude supplemental type certificate (STC) ST010697SE, all initial compliance times specified in flight cycles must be reduced to half of those specified in that service bulletin, and all repeat interval compliance times specified in flight cycles must be reduced to one-quarter of those specified in that service bulletin.+

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 the Proposed AD and the Service Information.’’ Similar Rulemaking

The crown skin panels on Model 737– 700 and –700C series airplanes are of a similar design to those on Model 737– 300, –400, –500, –600, –800, –900, and –900ER series airplanes. Therefore, all these models may be subject to the identified unsafe condition. We are considering similar rulemaking for these additional models. Differences Between the Proposed AD and the Service Information

Boeing Service Bulletin 737–53–1310, dated October 20, 2011, specifies to contact the manufacturer for disposition of certain repair conditions, but this proposed 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.

Tables 2 through 7 in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, specify post-modification inspections at certain chem-mill step locations, which may be used in support of compliance with section 121.1109(c)(2) or 129.109(c)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 129.109(c)(2)). However, this NPRM does not propose to require those post-modification inspections. This difference has been coordinated with Boeing. Costs of Compliance

We estimate that this proposed AD affects 545 airplanes of U.S. registry.

We estimate the following costs to comply with this proposed AD:



### E STIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. operators

Inspection of chem-mill step locations. 37 work-hours × $85 per hour = $3,145 per inspection cycle. None ... $3,145 per inspection cycle ...... $1,714,025 per 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.


### 57538 Federal Register / Vol. 77, No. 181 / Tuesday, September 18, 2012 / Proposed Rules

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** 

1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD):
The Boeing Company: Docket No. FAA– 2012–0936; Directorate Identifier 2011– NM–269–AD.

(a) Comments Due Date We must receive comments by November 2,
2012.
(b) Affected ADs

None.
(c) Applicability

This AD applies to The Boeing Company Model 737–700 and –700C series airplanes, as identified in Boeing Service Bulletin 737– 53–1310, dated October 20, 2011.
(d) Subject

Joint Aircraft System Component (JASC)/ Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Unsafe Condition

This AD was prompted by reports of early fatigue cracks at chem-mill areas on the crown skin panels. We are issuing this AD to detect and correct fatigue cracking of the skin panel at the specified chem-mill step locations, which could result in rapid decompression of the airplane.
(f) Compliance

Comply with this AD within the compliance times specified, unless already done. (g) Inspections At the applicable time specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, except as required by paragraph (j) of this AD: Do an external detailed inspection and an external non-destructive inspection (a medium frequency eddy current (MFEC), magneto optic imager (MOI), C-scan, or ultrasonic phased array (UTPA) inspection) for cracking in the fuselage skin along the chem-mill steps at certain locations specified in, and in accordance with, Boeing Service Bulletin 737–53–1310, dated October 20, 2011. Repeat the inspections required by paragraph (g) of this AD thereafter at the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1310, dated October 20, 2011.
(h) Repair

If any cracking is found during any inspection required by paragraph (g) of this AD, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (l) of this AD. Accomplishing the repair approved in accordance with the procedures specified in paragraph (l) of this AD terminates the repetitive inspection requirement for that area under the repair only.
(i) Optional Terminating Modification

Modification of an inspection area, including an external detailed inspection and an external non-destructive inspection (MFEC, MOI, C-scan, or UTPA) for cracking of the area to be modified, and a high frequency eddy current inspection of all existing holes for cracking, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, terminates the repetitive inspections required by paragraph (g) of this AD for that area only. If any cracking is found during any inspection described by this paragraph, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (l) of this AD.
(j) Service Bulletin Exception

Boeing Service Bulletin 737–53–1310, dated October 20, 2011, specifies compliance times ‘‘after the original issue date of this service bulletin.’’ However, this AD requires compliance within the specified compliance times ‘‘after the effective date of this AD.’’
(k) Post-Modification Inspections

The post-modification inspections specified in Tables 2 through 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, are not required by this AD.

Note 1 to paragraph (k) of this AD: The damage tolerance inspections specified in Tables 2 through 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, may be used in support of compliance with section 121.1109(c)(2) or 129.109(c)(2) of the Federal Aviation Regulations (14 CFR 121.1109(c)(2) or 14 CFR 129.109(c)(2)). The actions specified in Part 5 of the Accomplishment Instructions and corresponding figures of Boeing Service Bulletin 737–53–1310, dated October 20, 2011, are not required by this AD.

(l) 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 the Related Information section of this AD. Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov.

(2) Before using any approved AMOC, notify your appropriate principal inspector, or lacking a principal inspector, the manager of the local flight standards district office/ certificate holding district office.

(3) An AMOC that provides an acceptable level of safety may be used for any repair 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. For a repair method to be approved, the repair must meet the certification basis of the airplane, and the approval must specifically refer to this AD.

(m) Related Information

(1) For more information about this AD, contact Wayne Lockett, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6447; fax: (425) 917– 6590; email: Wayne.Lockett@faa.gov.

(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 review copies of the referenced service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, Washington. For information on the availability of this material at the FAA, call

425–227–1221.

Issued in Renton, Washington, on September 4, 2012. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–22891 Filed 9–17–12; 8:45 am]

**BILLING CODE 4910–13–P**