## 57990 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations

pounds; turkeys and all other poultry— 3 pounds.

* * * * *

Dated: September 13, 2012. David R. Shipman, Administrator, Agricultural Marketing

Service.

[FR Doc. 2012–23083 Filed 9–18–12; 8:45 am]

**BILLING CODE 3410–02–P**



### NATIONAL CREDIT UNION
**ADMINISTRATION**

**12 CFR Part 741**

**RIN 3133–AD66**



### Interest Rate Risk Policy and Program

Correction

In rule document 2012–02091, appearing on pages 55155–5167 in the issue of Thursday, February 2, 2012, make the following corrections:

1. On page 5157, in the second column, in the first line, the text entry ‘‘by asset size cohort at year-end 2010, as depicted in Table 1:’’ is deleted.

2. On page 5164, in the second column, under the heading ‘‘Account Attributes’’ on the second line, ‘‘P\principal’’ should read ‘‘Principal’’.

[FR Doc. C1–2012–2091 Filed 9–18–12; 8:45 am]

**BILLING CODE 1505–01–D**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0645; Directorate Identifier 2011–NM–052–AD; Amendment**  **39–17190; AD 2012–18–13]**

**RIN 2120–AA64**



### Airworthiness Directives; The Boeing **Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for all The Boeing Company Model 737– 100, –200, –200C, –300, –400, and –500 series airplanes. That AD currently requires repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft
fastener row attachment to the ‘‘Y’’ chord, and corrective actions if necessary. This new AD adds various inspections for discrepancies at the aft pressure bulkhead, and related investigative and corrective actions if necessary. This AD was prompted by several reports of fatigue cracking at that location. We are issuing this AD to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.

**DATES** 

### : This AD is effective October 24,

2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 24, 2012.

The Director of the Federal Register approved the incorporation by reference of certain other publications listed in this AD as of May 10, 1999 (64 FR 19879, April 23, 1999).

**ADDRESSES** 

### : For service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 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 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** 

### : Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057–3356; phone: (425) 917–6450; fax: (425) 917–6590; email: alan.pohl@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to supersede AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999). That AD applies to the specified products. The NPRM published in the Federal Register on June 28, 2012 (77 FR 38547). That NPRM proposed to continue to require repetitive inspections to detect cracking in the web of the aft pressure bulkhead at body station 1016 at the aft fastener row attachment to the ‘‘Y’’ chord, and corrective actions if necessary. That NPRM also proposed to require adding various inspections for discrepancies at the aft pressure bulkhead, and related investigative and corrective actions if

necessary.

Comments

We gave the public the opportunity to participate in developing this AD. We
have considered the comments received. Boeing supports the NPRM (77 FR 38547, June 28, 2012). Aviation Partners Boeing stated that it has reviewed the
NPRM and has determined that the installation of winglets per supplemental type certificate
ST01219SE does not affect the NPRM.

Conclusion

We reviewed the relevant data, considered the comments received, and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD affects 566 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

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

Low frequency eddy current (LFEC) inspection [retained actions from AD 99-08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999)]. 8 work-hours × $85 per hour = $680 ..... $0 $680 ....................... $384,880.


## 57991 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations

E STIMATED 

### C OSTS

### —Continued

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

Detailed visual inspection [retained actions from AD 99-08-23, Amendment 39–11132 (64 FR 19879, April 23, 1999)]. 2 work-hours × $85 per hour = $170 ..... 0 170 ......................... 96,220.

Detailed, high frequency eddy current

inspection, and LFEC inspections of
the web at the ‘‘Y’’ chord of the bulkhead, the web located under the outer circumferential tear strap, the ‘‘Z’’ stiffeners at the dome cap, and existing repairs [new action]. Up to 60 work-hours × $85 per hour = $5,100 per inspection cycle. 0 5,100 per inspection cycle. 2,886,600 per inspection cycle.



### We estimate the following costs to do any necessary on-condition inspections that would be required based on the results of the initial inspection. We have no way of determining the number of aircraft that might need these inspections:



### O N 

### -CONDITION 

### C OSTS

Action Labor cost Parts cost Cost per product

Detailed and HFEC inspections for oil-canning ........... 1 work-hour × $85 per hour = $85 ............................... $0 $85 LFEC or HFEC inspections for cracking ...................... 2 work-hours × $85 per hour = $170 ........................... 0 170



### We have received no definitive data that would enable us to provide cost estimates for the crack repairs specified
in this 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 have determined that 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, 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**

■ 

### 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 removing airworthiness directive (AD) 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999), and adding the following new AD:

2012–18–13 The Boeing Company: Amendment 39–17190; Docket No. FAA–2012–0645; Directorate Identifier

2011–NM–052–AD.

(a) Effective Date

This airworthiness directive (AD) is effective October 24, 2012.

(b) Affected ADs

This AD supersedes AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999).

(c) Applicability

This AD applies to all The Boeing Company Model 737–100, –200, –200C, –300, –400, and –500 series airplanes; certificated in any category.

(d) Subject

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

(e) Unsafe Condition

This AD was prompted by several reports of fatigue cracks in the aft pressure bulkhead. We are issuing this AD to detect and correct such fatigue cracking, which could result in rapid decompression of the fuselage.

(f) Compliance

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

(g) Retained Initial Inspection

This paragraph restates the initial inspection required by paragraph (a) of AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999). Perform either


## 57992 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations

inspection specified by paragraph (g)(1) or (g)(2) of this AD at the time specified in paragraph (h) of this AD.

(1) Perform a low frequency eddy current (LFEC) inspection from the aft side of the aft pressure bulkhead to detect discrepancies (including cracking, misdrilled fastener holes, and corrosion) of the web of the upper section of the aft pressure bulkhead at body
station 1016 at the aft fastener row attachment to the ‘‘Y’’ chord, from stringer 15 left (S–15L) to stringer 15 right (S–15R), in accordance with Boeing 737 Nondestructive Test Manual D6–37239, Part 6, Section 53– 10–54, dated December 5, 1998.

(2) Perform a detailed visual inspection of
the aft fastener row attachment to the ‘‘Y’’
chord from the forward side of the aft pressure bulkhead to detect discrepancies (including cracking, misdrilled fastener holes, and corrosion) of the entire web of the aft pressure bulkhead at body station 1016.

(h) Retained Compliance Times

This paragraph restates the compliance times specified in paragraph (b) of AD 99– 08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999). Perform the inspection required by paragraph (g) of this AD at the time specified in paragraph (h)(1), (h)(2), or (h)(3) of this AD, as applicable.

(1) For airplanes that have accumulated 40,000 or more total flight cycles as of May 10, 1999 (the effective date of AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999)): Inspect within 375 flight cycles or 60 days after May 10, 1999 (the effective date of AD 99–08–23), whichever occurs later.

(2) For airplanes that have accumulated 25,000 or more total flight cycles and fewer than 40,000 total flight cycles as of May 10, 1999 (the effective date of AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999)): Inspect within 750 flight cycles or 90 days after May 10, 1999 (the effective date of AD 99–08–23), whichever occurs later.

(3) For airplanes that have accumulated fewer than 25,000 total flight cycles as of May 10, 1999 (the effective date of AD 99– 08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999)): Inspect prior to the accumulation of 25,750 total flight cycles.

(i) Retained Repetitive Inspections

This paragraph restates the repetitive inspections required by paragraph (c) of AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999). Within 1,200 flight cycles after performing the initial inspection required by paragraph (g) of this AD, and thereafter at intervals not to exceed 1,200 flight cycles: Perform either inspection specified by paragraph (g)(1) or (g)(2) of this

AD.

(j) Retained Corrective Actions

This paragraph restates the corrective actions required by paragraph (d) of AD 99– 08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999). If any discrepancy is detected during any inspection required by paragraph (g), (h), or (i) of this AD: Prior to further flight, accomplish the actions specified by paragraphs (j)(1) and (j)(3) of this AD, and paragraph (j)(2) of this AD, if applicable. (1) Perform a high frequency eddy current inspection from the forward side of the bulkhead to detect cracking of the web at the ‘‘Y’’ chord attachment, around the entire periphery of the ‘‘Y’’ chord, in accordance with Boeing 737 Nondestructive Test Manual D6–37239, Part 6, Section 51–00–00, Figure 23, dated November 5, 1995.

(2) If the most recent inspection performed in accordance with paragraph (g) of this AD was not a detailed visual inspection: Accomplish the actions specified by paragraph (g)(2) of this AD. If the inspection was a detailed visual inspection, it is not necessary to repeat that inspection prior to further flight.

(3) Repair any discrepancy such as cracking or corrosion or misdrilled fastener holes using a method approved in accordance with the procedures specified in paragraph (u) of this AD.

(k) New Requirements: Inspections of the Web at the ‘‘Y’’ Chord Upper Bulkhead From

S–15L to S–15R

At the later of the times specified in paragraphs (k)(1) and (k)(2) of this AD: Do detailed and LFEC inspections of the aft side of the bulkhead web, or do detailed and HFEC inspections from the forward side of the bulkhead, and do all applicable related investigative and corrective actions; in
accordance with Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraphs (r)(1) and (r)(3) of this AD. Inspect for cracks, incorrectly drilled fastener holes, and elongated fastener holes. Do all applicable related investigative and corrective actions before further flight. Repeat the inspections at the applicable times specified in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011.

(1) Prior to the accumulation of 25,000 total flight cycles.

(2) Except as required by paragraphs (r)(2) and (r)(4) of this AD, at the later of the times specified in the ‘‘Compliance Time’’ column in table 1 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1214, Revision 4, dated December 16,

2011.

(l) New Requirements: Inspections of the
Web at the ‘‘Y’’ Chord in the Lower
Bulkhead From S–15L to S–15R

Except as required by paragraphs (r)(2) and (r)(5) of this AD, at the applicable time specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do detailed and eddy current inspections of the web from the forward or aft side of the bulkhead for cracks, incorrectly drilled fasteners, and elongated fasteners, in accordance with Part III of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraphs (r)(1) and (r)(3) of this AD. If any crack, incorrectly drilled fastener, elongated fastener, or corrosion is found, before further flight, repair the web using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Repeat the inspections at the applicable times specified in table 2 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011.

(m) New Requirements: One-Time Inspection Under the Tear Strap

Except as required by paragraphs (r)(2) and (r)(5) of this AD, at the applicable time specified in table 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do a one-time LFEC inspection for cracks on the aft side of the
bulkhead of the web located under the outer circumferential tear strap, or do a one-time HFEC inspection for cracks from the forward
side of the bulkhead of the web located under the outer circumferential tear strap, in
accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(1) of this AD. If any cracking is found, before further flight, repair the bulkhead using a method approved in accordance with the procedures specified in paragraph (u) of this AD.

(n) New Requirements: Inspection for OilCanning

Except as required by paragraph (r)(2) of this AD, at the applicable time specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do a detailed inspection from the aft side of the bulkhead for oil-canning and do all applicable related investigative and corrective actions, in accordance with Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(1) of this AD. Do all related investigative and corrective actions before further flight. Thereafter, repeat the inspection at the applicable times specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011. For oil-cans found within the limits specified in Part II of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: In lieu of installing the repair before further flight, at the applicable times specified in table 4 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, do initial and repetitive detailed and HFEC inspections for cracks of the oil-canning and install the repair, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011. If any crack is found, before further flight, repair the cracking using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Installing the repair terminates the repetitive inspections for
cracks.


## 57993 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations

(o) New Requirements: Inspection of the Dome Cap at the Center of the Bulkhead

Except as required by paragraphs (r)(2) and (r)(5) of this AD, at the applicable time specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do an eddy current inspection to detect any cracking of the dome cap at the center of the bulkhead, and do all applicable corrective actions, in accordance with Part IV of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011. Do all corrective actions before further flight. Repeat the inspection at the times specified in table 5 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011.

(p) New Requirements: Inspection of the Forward Flange of the ‘‘Z’’ Stiffeners at the Dome Cap

Except as required by paragraphs (r)(2) and (r)(5) of this AD, at the applicable time specified in table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do an HFEC inspection to detect any cracking of the ‘‘Z’’ stiffener flanges at the dome cap in the center of the bulkhead, in accordance with Part V of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(1) of this AD. If any crack is found, before further flight, repair the flanges using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Repeat the inspection at the applicable times specified in table 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737– 53A1214, Revision 4, dated December 16,

2011.

(q) New Requirements: Inspection for Existing Repairs on the Bulkhead

Except as required by paragraph (r)(2) of this AD, at the applicable time specified in table 7 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Do a detailed inspection of the bulkhead web and stiffeners for existing repairs, in accordance with Part VI of the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(1) of this AD.

(1) If any repair identified in the ‘‘Condition’’ column of table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, is found and the ‘‘Reference’’ column refers to Appendix A, B, C, or D of that service bulletin: At the applicable times specified in table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(2) of this AD, do a HFEC inspection or a LFEC inspection of the web for cracking, in accordance with Appendix A, B, C, or D, as applicable, of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011. If any cracking is found, before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD. Repeat the inspections, thereafter, at the applicable intervals specified in table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011.

(2) If any repair identified in the ‘‘Condition’’ column of table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, is found and the ‘‘Reference’’ column refers to Appendix E of that service bulletin: At the applicable times specified in table 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, except as required by paragraph (r)(2) of this AD, remove the repair and replace with a new repair, in accordance with Appendix E of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011.

(3) If any non-SRM (structural repair manual) repair is found and the repair does not have FAA-approved damage tolerance inspections, except as required by paragraph (r)(2) of this AD, at the applicable time specified in table 7 of Paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011: Contact the Boeing Commercial Airplanes Organization Designation Authorization (ODA) that has been authorized by the Manager, Seattle Aircraft Certification Office, for damage tolerance inspections. Do those damage tolerance inspections at the times given using a method approved in accordance with the procedures specified in paragraph (u) of this

AD.

(r) Exceptions to the Service Information

(1) Where Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, specifies to contact Boeing for repair instructions: Before further flight, repair using a method approved in accordance with the procedures specified in paragraph (u) of this AD.

(2) Where Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, specifies a compliance time ‘‘after
the date of Revision 1 to this service bulletin,’’ ‘‘from the date of Revision 3 of this service bulletin,’’ ‘‘after the date of Revision 3 to this service bulletin,’’ or ‘‘of the effective date of AD 99–08–23,’’ this AD requires compliance within the specified compliance
time after the effective date of this AD.

(3) Access and restoration procedures specified in the Accomplishment Instructions of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, are not required by this AD. Operators may do those procedures following their maintenance practices.

(4) Where table 1 of paragraph 1.E., ‘‘Compliance’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, specifies a compliance
time relative to actions done ‘‘in accordance with paragraph (a)(2) of AD 99–08–23,’’ this AD requires compliance within the specified compliance time relative to actions specified in paragraph (g)(2) of this AD.

(5) Where the Condition columns in tables 2, 3, 5, and 6 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 737–53A1214, Revision 4, dated December 16, 2011, refer to total flight cycles, this AD applies to the airplanes with the specified total flight cycles as of the effective
date of this AD.

(s) Terminating Action

Accomplishment of the requirements of paragraphs (k) through (q) of this AD terminates the requirements of paragraphs (g) through (j) of this AD.

(t) Credit for Previous Actions

This paragraph provides credit for the actions required by paragraphs (k) through (s) of this AD, if the actions were performed before the effective date of this AD using the service bulletins specified in paragraphs (t)(1) through (t)(4) of this AD.

(1) Boeing Alert Service Bulletin 737– 53A1214, dated June 17, 1999.

(2) Boeing Alert Service Bulletin 737– 53A1214, Revision 1, dated June 22, 2000.

(3) Boeing Alert Service Bulletin 737– 53A1214, Revision 2, dated May 24, 2001.

(4) Boeing Alert Service Bulletin 737– 53A1214, Revision 3, dated January 19, 2011.

(u) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Seattle 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 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.

(4) AMOCs approved previously in accordance with AD 99–08–23, Amendment 39–11132 (64 FR 19879, April 23, 1999), are approved as AMOCs for the corresponding provisions of this AD.

(v) Related Information

For more information about this AD, contact Alan Pohl, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, Washington 98057– 3356; phone: (425) 917–6440; fax: (425) 917– 6590; email: alan.pohl@faa.gov.


## 57994 Federal Register / Vol. 77, No. 182 / Wednesday, September 19, 2012 / Rules and Regulations

(w) 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.

(3) The following service information was approved for IBR on October 24, 2012.

(i) Boeing Alert Service Bulletin 737– 53A1214, Revision 4, dated December 16,

2011.

(ii) Reserved. (4) The following service information was approved for IBR on May 10, 1999 (64 FR 19879, April 23, 1999).

(i) Boeing 737 Nondestructive Test Manual D6–37239, Part 6, Section 53–10–54, dated December 5, 1998.

(ii) Boeing 737 Nondestructive Test Manual D6–37239, Part 6, Section 51–00–00, Figure 23, dated November 5, 1995.

(5) For The Boeing Company service information identified in this AD, contact Boeing Commercial Airplanes, Attention: Data & Services Management, P.O. Box 3707, MC 2H–65, Seattle, Washington 98124–2207; telephone 206–544–5000, extension 1; fax
206–766–5680; Internet https://www. myboeingfleet.com.

(6) 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.

(7) You may view this service information that is incorporated by reference 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 Renton, Washington, on August

31, 2012.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2012–22334 Filed 9–18–12; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0644; Directorate Identifier 2012–NM–011–AD; Amendment**  **39–17193; AD 2012–18–16]**

**RIN 2120–AA64**



### Airworthiness Directives; The Cessna **Aircraft Company Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain The Cessna Aircraft Company Model 750 airplanes. This AD was prompted by reports of direct current (DC) generator overvoltage events. This AD requires replacing the auxiliary power unit (APU) generator control unit (GCU). We are issuing this AD to prevent DC generator overvoltage events, which could result in smoke in the cockpit and loss of avionics and electrical systems.

**DATES** 

### : This AD is effective October 24,

2012.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in the AD as of October 24, 2012.

**ADDRESSES** 

### : For service information identified in this AD, contact Cessna Aircraft Co., P.O. Box 7706, Wichita, Kansas 67277; telephone 316–517–6215; fax 316–517–5802; email citationpubs@cessna.textron.com;

Internet https:// www.cessnasupport.com/newlogin.html. You may review copies of the
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.
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 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** 

### : Christine Abraham, Aerospace Engineer, Electrical Systems and Avionics Branch, ACE–119W, FAA, Wichita Aircraft Certification Office, 1801 Airport Road, Room 100, Mid-Continent Airport, Wichita, Kansas 67209; telephone: 316– 946–4165; fax: 316–946–4107; email: christine.abraham@faa.gov.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM published in the Federal Register on June 25, 2012 (77 FR 37827). That NPRM proposed to require replacing the auxiliary power unit (APU) generator control unit (GCU).

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 37827, June 25, 2012) or on the determination of the cost to the public.

Conclusion

We reviewed the relevant data and determined that air safety and the public interest require adopting the AD as proposed.

Costs of Compliance

We estimate that this AD affects 58 airplanes of U.S. registry.

We estimate the following costs to comply with this AD:



### E STIMATED 

### COSTS

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

Replacement ....................................... 2 work-hours × $85 per hour = $170 ......................... $2,400 $2,570 $149,060



### According to the manufacturer, all of the costs of this AD may be covered under warranty, thereby reducing the cost impact on affected individuals. We do not control warranty coverage for affected individuals. As a result, we
have included all costs in our cost

estimate. 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