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the part’s TIS. The part numbers listed in Table 2 to paragraph (e)(2) of this AD are not eligible for installation on any helicopter.



### T ABLE 

### 2 TO 

### P ARAGRAPH 

### (e) OF 

### T HIS



### AD—P ARTS 

### T O 

### B E 

### R EMOVED 

### F ROM 

### S ERVICE

Part name P/N

Rod and bushing assembly, M/R. 6410–21090–

011
M/R blade .......................... 6415–20001– 013, –014, or

–015 Pylon stabilizer .................. 6420–66201– 010, –014, or

–015 M/R shaft assembly ........... 6435–20078–

013Oil cooler and support assembly. 6435–60050–

043 Pitch change link, rotary

rudder. 65113–07100–

046 Spindle, M/R blade ............ S1510–23070–3

(3) Within 20 hours TIS, and thereafter at intervals not to exceed 20 hours TIS, visually inspect each M/R servo and control arm assembly, P/N S1565–20421–10, –11, –041, or –043, and determine if there is any oil leaking from the M/R tandem servo housing assembly (servo housing), P/N S1565–20252– 2. If there is any oil leaking from the servo housing, before further flight, replace the M/ R servo and control arm assembly.

(4) Within 20 hours TIS or before reaching 1,120 hours TIS, whichever occurs later, and
thereafter at intervals not to exceed 200 hours TIS or 12 months, whichever occurs first, ultrasonic (UT) inspect each M/R hub horizontal hinge pin (hinge pin), P/N S1510– 23099–1 or P/N S1510–23099–001, for a
crack in accordance with the Accomplishment Instructions, paragraphs 2.A through 2.C, of Erickson Service Bulletin (SB) No. 64B10–3, Revision D, dated October 15, 2007, except you are not required to contact Erickson nor send hinge pins to them. A non-destructive testing (NDT) UT Level I Special, Level II, or Level III inspector who is qualified under the guidelines established by ASNT SNT–TC–1A, ISO 9712, or an FAA-accepted equivalent qualification standard for NDT inspection and evaluation, must perform the UT inspection.

(5) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, perform a fluorescent-magnetic particle inspection (MPI) of each second stage planetary plate assembly, P/N 6435–20231– 016, for a crack.

(6) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and
thereafter at intervals not to exceed 650 hours TIS, perform an MPI of each M/R shaft, P/N 6435–20078–104, for a crack, paying particular attention to the lower spline area.

(7) Within 150 hours TIS or before reaching 1,450 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 1,450 hours TIS, perform an MPI of each M/R shaft, P/N 6435–20078–105, for a crack, paying particular attention to the lower spline area.

(8) Within 150 hours TIS or before reaching 3,375 hours TIS, whichever occurs later, and thereafter at intervals not to exceed 3,375 hours TIS, perform a fluorescent penetrant inspection of each housing lug on each servo housing, P/N S1565–20252–2, for a crack.

(9) At each overhaul of the main gearbox assembly, P/N 6435–20400–053, –054, –058,

–060, –062, –063, –064, –065, or –066, perform an MPI of the entire shaft of each M/R shaft assembly, P/N 6435–20078–014, –015, or –016, for a crack, paying particular attention to the rotating swashplate spherical bearing ball travel area, which is located approximately ten inches above the upper roller bearing journal shoulder.

(10) If there is a crack in any part, before further flight, replace the cracked part.

(11) At each overhaul of the damper assembly, P/N 6410–26200–042, replace the following parts with airworthy parts that have zero (0) hours TIS:

(i) All Air Force-Navy Aeronautical Standard (AN), Aerospace Standard (AS), Military Standard (MS), and National Aerospace Standard (NAS) nuts, bolts, washers, and packings, except packing, P/N MS28775–011, installed on stud, P/N SHF111–11SN–12A;

(ii) Lock washer, P/N SS5073–2; (iii) Nut, P/N SS5081–05; (iv) Felt seal, P/N S1510–26017; (v) Retaining ring, P/N UR106L; and (vi) Nut, P/N 6410–26214–101.

(f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Rotorcraft Certification Office, FAA, may approve AMOCs for this AD. Send your proposal to: Michael Kohner, Aerospace Engineer, Rotorcraft Certification Office, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5170; email 7-avs-asw170@faa.gov

.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.

(g) Additional Information

Erickson Service Bulletin (SB) No. 64B General-1, Revision 19, dated September 15, 2010, which is not incorporated by reference,
contains additional information about the subject of this AD. For service informationidentified in this AD, contact Erickson AirCrane Incorporated, ATTN: Chris Erickson/ Compliance Officer, 3100 Willow Springs Rd, PO Box 3247, Central Point, OR 97502, telephone (541) 664–5544, fax (541) 664– 2312, email address
cerickson@ericksonaircrane.com . You may review a copy of this information at the FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137.

(h) Subject

Joint Aircraft Service Component (JASC) Code: 6200: Main Rotor System; 6300: Main Rotor Drive System; 6410: Tail Rotor Blades; 6500: Tail Rotor Drive System. Issued in Fort Worth, Texas, on May 17,

2013. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.

[FR Doc. 2013–12523 Filed 5–24–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2013–0425; Directorate Identifier 2012–NM–224–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 747 airplanes. This proposed AD was prompted by reports of cracking in the forward and aft inner chord of the body station (BS) 2598 bulkhead near the upper corners of the cutout for the horizontal stabilizer rear spar, and cracking in the bulkhead upper and lower web panels near the inner chord to shear deck connection. This proposed AD would require doing repetitive inspections for cracking in the bulkhead splice fitting, frame supports, forward and aft inner chords, and floor support; doing an inspection for cracking in the bulkhead upper web, doubler, and bulkhead lower web; and corrective actions if necessary; for certain airplanes, inspections for cracking in the repaired area of the bulkhead, and corrective actions if necessary; for certain airplanes, support frame modification and support frame inspections, and related investigative and corrective actions, if necessary; for certain airplanes, repetitive support frame post-modification inspections and inspections for cracking in the hinge support, and related investigative and corrective actions if necessary; for certain airplanes, a one-time inspection of the frame web and upper shear deck (floor support) chord aft side for fasteners; and a one-time inspection of the upper forward inner chord, frame support fitting and splice fitting, for the installation of certain fasteners; and related investigative and corrective actions if necessary; for certain airplanes, a one-time inspection of the upper forward inner chord, frame


## 31868 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules

support fitting and splice fitting for theinstallation of certain fasteners; a onetime inspection for any repair installed on the left and right side of the aft inner chord, and related investigative and corrective actions, if necessary; for certain airplanes, a one-time inspection of the support frame outer chord for cracking, and repair if necessary; and repetitive support frame post-repair inspections, and corrective actions, if necessary. We are proposing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity of the bulkhead and the horizontal stabilizer support structure and result in loss of controllability of the airplane.

**DATES** 

### : We must receive comments on this proposed AD by July 12, 2013.

**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, 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 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** 

### : Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917– 6590; email: bill.ashforth@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– 2013–0425; Directorate Identifier 2012– NM–224–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 cracking in the
forward and aft inner chord of the BS 2598 bulkhead near the upper corners of
the cutout for the horizontal stabilizer rear spar, and cracking in the bulkhead upper and lower web panels near the
inner chord to shear deck connection. This condition, if not corrected, could result in fatigue cracking of the BS 2598 bulkhead structure, which could result in inability of the structure to carry horizontal stabilizer flight loads, and loss of controllability of the airplane.

Relevant Service Information

We reviewed Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011; and Boeing Alert Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011. For information on the procedures and compliance times, see this service
information at http:// www.regulations.gov by searching for
Docket No. FAA–2013–0425.

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.’’

The phrase ‘‘related investigative actions’’ might be used in this proposed AD. ‘‘Related investigative actions’’ are follow-on actions that: (1) Are related to the primary actions, and (2) are actions that further investigate the nature of any condition found. Related investigative actions in an AD could include, for example, inspections.

In addition, the phrase ‘‘corrective actions’’ might be used in this proposed

AD. ‘‘Corrective actions’’ are actions that correct or address any condition
found. Corrective actions in an AD could include, for example, repairs.

Differences Between the Proposed AD
and the Service Information

Where Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies accomplishing inspections for cracks in forward and aft inner chords, splice fittings, floor supports, and upper and lower web panels, this AD also requires doing an open-hole high frequency eddy current (HFEC) inspection of the doubler. Figure 2 of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, includes the inspections.

Where paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747– 53A2427, Revision 6, dated July 14, 2011; or 747–53A2473, Revision 4, dated December 1, 2011; specify to contact Boeing for repair data and do the repair, this AD requires doing those repairs in accordance with a method approved by the FAA.

If cracking is found in any doubler during any inspection specified by paragraph (g) of this proposed AD, this proposed AD would require repairing using a method approved in accordance with the procedures specified in paragraph (o) of this AD.

Costs of Compliance

We estimate that this proposed AD affects 165 airplanes of U.S. registry.

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


## 31869 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules

E STIMATED 

### C OSTS

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

Inspection ...................................... 24 work-hours × $85 per hour = $2,040 per inspection cycle. $0 $2,040 per inspection cycle. $336,600 per inspection cycle.

Support frame modification ........... 315 work-hours × $85 per hour = $26,775. 0 $26,775 ............ Up to $4,417,875.

Support frame upper corner fastener inspection. 16 work-hours × $85 per hour = $1,360. 0 $1,360 .............. Up to $224,400.

Support frame post-modification

inspection. 200 work hours × $85 per hour = $17,000. 0 $17,000 ............ $2,805,000.



### We have received no definitive data that would enable us to provide a cost
estimate 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**

■ 

### 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– 2013–0425; Directorate Identifier 2012–

NM–224–AD.

(a) Comments Due Date

We must receive comments by July 12,

2013.

(b) Affected ADs

This AD affects AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010).

(c) Applicability

This AD applies to The Boeing Company Model 747–100, 747–100B, 747–100B SUD, 747–200B, 747–200C, 747–200F, 747–300, 747–400, 747–400D, 747–400F, 747SR, and 747SP series airplanes, certificated in any category, as identified in Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 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 cracking in the forward and aft inner chord of the body station (BS) 2598 bulkhead near the upper corners of the cutout for the horizontal stabilizer rear spar, and cracking in the bulkhead upper and lower web panels
near the inner chord to shear deck connection. We are issuing this AD to detect and correct fatigue cracking of the BS 2598 bulkhead structure, which could adversely affect the structural integrity of the bulkhead and the horizontal stabilizer support structure and result in loss of controllability of the airplane.

(f) Compliance

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

(g) Inspections of the Bulkhead (Support Frame)

For airplanes on which the bulkhead (support frame) modification specified in Boeing Service Bulletin 747–53A2473 has not been accomplished: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, except as provided by paragraph (m)(1), (m)(2), or (m)(3), as applicable, of this AD, do an open-hole and surface high frequency eddy current (HFEC) inspection for cracking in the bulkhead (support frame) which includes the bulkhead splice fitting, frame supports, forward and aft inner chords, and floor support; do a surface HFEC inspection for cracking in the bulkhead upper web and doubler; do an open-hole and surface HFEC inspection for cracking in the bulkhead lower web; and do all applicable corrective actions; in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, except as required by paragraphs (m)(4), (m)(5) and (m)(6) of this AD, and except as provided by paragraph (h) of this AD. Do all applicable corrective actions before further flight. Repeat the applicable inspections, thereafter, at the applicable times in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011. Doing the modification required by paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.

(h) Interim Modification

For airplanes in groups 1 and 2 as identified in Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, on which no cracking was found during any inspection required by paragraph (g) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, except as provided by paragraph (m)(2) of this AD, do the interim modification, in accordance with


## 31870 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules

the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011. Doing the
interim modification terminates the repetitive inspection requirement of paragraph (g) of this AD in the area of the modification only. The repetitive inspections of the bulkhead lower web, as specified in paragraph (g) of this AD, must be done. If the aft inner chord repair or upper web repair specified in Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, has been accomplished, an interim modification on the side of the airplane that has the repair is not required by this paragraph.

(i) Post-Repair Inspection or Post-Interim Modification Inspection

For airplanes on which an interim modification, or aft inner chord repair, or upper web repair has been done as specified in paragraph (g) or (h) of this AD: At the applicable times specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, except as specified in paragraph (m)(1), (m)(2), or (m)(3), as applicable, of this AD, do the actions specified in paragraph (i)(1) and (i)(2) of this AD, and all applicable corrective actions, in accordance with the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable corrective actions before further flight. Repeat the inspections thereafter at the applicable intervals specified in paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011. Doing the modification required by paragraph (j) of this AD terminates the repetitive inspections required by this paragraph.

(1) Do forward side surface HFEC inspections for cracking of the bulkhead forward inner chord, splice fitting, and frame support.

(2) Do surface and open-hole HFEC inspections for cracking in the repaired area
of the bulkhead.

(j) Bulkhead (Support Frame) Modification and Inspections

For airplanes on which the bulkhead (support frame) modification specified in Boeing Alert Service Bulletin 747–53A2473, dated March 24, 2005; Revision 1, dated February 20, 2007; Revision 2, dated August 28, 2009; Revision 3, dated July 14, 2011; or Revision 4, dated December 1, 2011, has not
been done as of the effective date of this AD: At the applicable time in tables 2 and 3 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Alert Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do the bulkhead (support frame) modification and inspections and all applicable related investigative and corrective actions; in accordance with steps 3.B.3., 3.B.4., and 3.B.5. of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions before further flight. Doing the modification in this paragraph terminates the inspections required by paragraphs (g) and (i) of this AD.

(k) Post Modification Inspections

(1) For airplanes on which the bulkhead (support frame) modification has been done as specified in Boeing Service Bulletin 747– 53A2473, dated March 24, 2005; Revision 1, dated February 20, 2007; Revision 2, dated August 28, 2009; Revision 3, dated July 14, 2011; or Revision 4, dated December 1, 2011: Except as provided by paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in tables 6, 7, 8, and 9 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do support frame post-modification inspections, and open-hole HFEC inspection for cracking in the hinge support, and do all applicable related investigative and corrective actions, in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4). Do all applicable related investigative and corrective actions before further flight. Repeat the inspections thereafter at the applicable times in tables 6, 7, 8, and 9 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011.

(2) For airplanes on which the support
frame modification has been done as specified in Boeing Service Bulletin 747– 53A2473, Revision 1, dated February 20, 2007: Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in tables 4 and 5 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time general visual inspection of the frame web and upper shear deck (floor support) chord aft side for fasteners that were installed as part of an inner chord repair removal; and a one-time general visual inspection of the upper forward inner chord, frame support fitting and splice fitting, for the installation of certain fasteners; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions at the applicable times specified in tables 4 and 5 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,

2011.

(3) For airplanes on which the support
frame modification has been done as specified in Boeing Service Bulletin 747– 53A2473, dated March 24, 2005: Except as specified in paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in tables 5 and 10 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time general visual inspection of the upper forward inner chord, frame support fitting, and splice fitting for the installation of certain fasteners; a one-time general visual inspection for any repair installed on the left and right side of the aft inner chord; and do all applicable related investigative and corrective actions; in accordance with the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, except as required by paragraph (m)(4) of this AD. Do all applicable related investigative and corrective actions at the applicable times specified in tables 5 and 10 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,

2011.

(4) For airplanes on which a postmodification inspection was done in accordance with paragraph 3.B.8. of Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 3, dated July 14, 2011: Except as required by paragraphs (m)(7) and (m)(8) of this AD, at the applicable time in table 11 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a one-time surface HFEC inspection of the support frame outer chord for cracking, in accordance with Part 1 of the Accomplishment Instructions of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011. If any cracking is found, repair before further flight, using a method approved in accordance with the procedures specified in paragraph (o) of
this AD.

(l) Post-Modification Post-Repair Inspections

For airplanes on which post-modification inspection cracks were repaired by doing theinstallation of an upper or lower corner postmodification web crack repair as specified in Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011: At the applicable times specified in tables 6 and 8 of paragraph 1.E., ‘‘Compliance’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, do a bulkhead (support frame) post-repair inspection, and do all applicable corrective actions, in accordance with paragraph a., b., or c. of Part 4 of paragraph 3.B.8 of the Accomplishment Instructions of Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, as applicable, except as required by paragraph (m)(4) of this AD. Repeat the inspection, thereafter, at the applicable times specified in tables 6 and 8 of paragraph 1.E., ‘‘Compliance,’’ of Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1,

2011.

(m) Exceptions

(1) Where Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies a compliance time after the date on Revision 2 of this service bulletin, this AD requires compliance within the specified compliance time as of August 28, 2001 (the effective date of AD 2001–15–03, Amendment 39–12337 (66 FR 38365, July 24, 2001)).

(2) Where Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies a compliance time after the date on Revision 4 of this service bulletin, this AD requires compliance within the specified compliance time as of April 13, 2006 (the effective date of AD 2006–05–06, Amendment 39–14503 (71 FR 12125, March 9, 2006)).


## 31871 Federal Register / Vol. 78, No. 102 / Tuesday, May 28, 2013 / Proposed Rules

(3) Where Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies a compliance time after the date on Revision 6 of this service bulletin, this AD requires compliance within the specified compliance time ‘‘after the effective
date of this AD.’’

(4) If any cracking is found during any inspection required by this AD, and Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011; or Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011; specifies to contact Boeing for appropriate action: Before further flight, repair the crack using a method approved in accordance with the procedures specified in paragraph (o) of this AD.

(5) If, during any inspection required by paragraph (g) of this AD, any cracking is found in the doubler, before further flight, repair, using a method approved in accordance with the procedures specified in paragraph (o) of this AD.

(6) Where Part 1 of the Accomplishment Instructions of Boeing Alert Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies accomplishing inspections for cracks for forward and aft inner chords, splice fittings, floor supports, and upper and lower web panels, this AD also requires doing an open-hole HFEC inspection of the
doubler.

(7) Where Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, specifies a compliance time after the date on Revision 2 of the service bulletin, this AD requires compliance within the specified compliance time as of August 5, 2010 (the effective date of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010)).

(8) Where Boeing Service Bulletin 747– 53A2473, Revision 4, dated December 1, 2011, specifies a compliance time after the
date on Revision 3 or 4 of the service bulletin, this AD requires compliance within the specified compliance time ‘‘after the
effective date of this AD.’’

(n) Terminating Action for Certain Requirements of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010)

(1) Accomplishing the inspections, repairs, and modification in accordance with Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, is a terminating action for the corresponding inspections, repairs, and modification at the STA 2598 support frame required by paragraphs (i), (j), (k)(1), (m), (n), (o), (p), (q), (r), (s), (t), (u), and (v) of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010). When Boeing Service Bulletin 747–53A2473, Revision 4, dated December 1, 2011, specifies to contact Boeing for repair instructions, the repair instructions must be approved by the FAA in accordance with paragraph (o) of this AD. All provisions of AD 2010–14–07 that are not specifically referenced in this paragraph remain fully applicable and must be complied with.

(2) Accomplishing the inspections, repairs
and interim modification in accordance with Boeing Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, is a terminating action for the corresponding inspections, repairs and interim modification at the STA 2598 bulkhead required by paragraphs (i), (j), (o), (s), (t), (u), and (v) of AD 2010–14–07, Amendment 39–16352 (75 FR 38001, July 1, 2010). When Boeing Service Bulletin 747–53A2427, Revision 6, dated July 14, 2011, specifies to contact Boeing for repair data, the repair data must be approved by the FAA in accordance with paragraph (o) of this AD. All provisions of AD 2010–14–07 that are not specifically reference in this paragraph remain fully applicable and must be complied with.

(o) 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.

(p) Related Information

(1) For more information about this AD, contact Bill Ashforth, Aerospace Engineer, Airframe Branch, ANM–120S, FAA, Seattle Aircraft Certification Office, 1601 Lind
Avenue SW., Renton, WA 98057–3356; phone: 425–917–6432; fax: 425–917–6590;
email: bill.ashforth@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, WA. For information on the availability of this material at the FAA, call 425–227–1221.

Issued in Renton, Washington, on May 17,

2013. Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.

[FR Doc. 2013–12618 Filed 5–24–13; 8:45 am]

**BILLING CODE 4910–13–P** 

### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 71**

**[Docket No. FAA–2013–0282; Airspace Docket No. 13–AAL–3]** 



### Proposed Amendment of Class E **Airspace; Gustavus, AK**

**AGENCY** 

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

**ACTION** 

### : Notice of proposed rulemaking (NPRM).

**SUMMARY** 

### : This action proposes to amend Class E airspace at Gustavus Airport, Gustavus, AK. Decommissioning of the Gustavus Nondirectional Radio Beacon (NDB) has made this action necessary for the safety and management of Instrument Flight Rules (IFR) operations at the airport. This action also would adjust the geographic coordinates of the airport.

**DATES** 

### : Comments must be received on or before July 12, 2013.

**ADDRESSES** 

### : Send comments on this proposal to the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590; telephone (202) 366–9826. You must identify FAA Docket No. FAA–2013– 0282; Airspace Docket No. 13–AAL–3, at the beginning of your comments. You may also submit comments through the

Internet at http://www.regulations.gov.

**FOR FURTHER INFORMATION CONTACT** 

### : Eldon Taylor, Federal Aviation Administration, Operations Support Group, Western Service Center, 1601 Lind Avenue SW., Renton, WA 98057; telephone (425) 203–4537.

**SUPPLEMENTARY INFORMATION** 

### :

Comments Invited

Interested parties are invited to participate in this proposed rulemaking by submitting such written data, views, or arguments, as they may desire. Comments that provide the factual basis supporting the views and suggestions presented are particularly helpful in developing reasoned regulatory decisions on the proposal. Comments are specifically invited on the overall regulatory, aeronautical, economic, environmental, and energy-related aspects of the proposal.

Communications should identify both docket numbers (FAA Docket No. FAA 2013–0282 and Airspace Docket No. 13– AAL–3) and be submitted in triplicate to the Docket Management System (see