49978 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 

For reasons set forth above, the DOE’s 

actions also violate the principles 

outlined in President Obama’s order. 

Conclusion 

Landmark respectfully requests DOE 

immediately halt implementation and 

rescind the Rule. In the alternative, 

Landmark requests DOE adhere to the 

mandates of the APA, and subject the 

changes documented in this Petition to 

a proper notice and comment. 

Respectfully Submitted, 

Mark R. Levin, President 

Landmark Legal Foundation, 19415 Deerfield 

Ave., Suite 312, Leesburg, VA 20176. 

JULY 2, 2013 

[FR Doc. 2013–19950 Filed 8–15–13; 8:45 am] 

BILLING CODE 6450–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0694; Directorate 

Identifier 2013–NM–097–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 supersede 

airworthiness directive (AD) 2002–10– 

11, which applies to certain the Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2002–10–11 currently requires 

repetitive inspections for cracking and 

corrosion of the aft pressure bulkhead, 

and corrective actions if necessary; and, 

for certain airplanes, enlargement of 

frame chord drain holes, and repetitive 

inspections of the frame chord drain 

path for debris, and corrective actions if 

necessary. Since we issued AD 2002– 

10–11, we have received three reports of 

severe corrosion in the area affected by 

that AD. This proposed AD would, for 

certain airplanes, reduce the repetitive 

inspection interval, and add repetitive 

inspections of the frame chord drain 

path for obstructions and debris, and 

corrective actions if necessary. This 

proposed AD would also limit corrosion 

and cracking repairs of the aft pressure 

bulkhead accomplished after the 

effective date of this AD to those 

approved by the FAA in a manner 

described therein. In reviewing AD 

2002–10–11, we noted that the drain 

path inspection was not required for 

certain airplanes, and could be 

eliminated for all airplanes if operators 

accomplished certain actions required 

by AD 2002–10–11. This proposed AD 

would add a drain path inspection for 

all airplanes. We are proposing this AD 

to detect and correct corrosion or 

cracking of the aft pressure bulkhead, 

which could result in loss of the aft 

pressure bulkhead web and stiffeners, 

and consequent rapid decompression of 

the airplane. 

DATES: We must receive comments on 

this proposed AD by September 30, 

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: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: 425–917–6450; fax: 

425–917–6590; email: alan.pohl@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0694; Directorate Identifier 

2013–NM–097–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 

On May 14, 2002, we issued AD 

2002–10–11, Amendment 39–12757 (67 

FR 36085, May 23, 2002), for certain 

Model 737–100, –200, –200C, –300, 

–400, and –500 series airplanes. AD 

2002–10–11 superseded AD 84–20–03 

R1, Amendment 39–5183 (50 FR 51235, 

December 16, 1985). AD 2002–10–11 

requires repetitive inspections for 

cracking and corrosion of the aft 

pressure bulkhead, and corrective 

actions if necessary; and, for certain 

airplanes, enlargement of frame chord 

drain holes, repetitive inspections of the 

frame chord drain path for obstructions 

and debris, and corrective actions if 

necessary. We issued AD 2002–10–11 to 

detect and correct corrosion or cracking 

of the aft pressure bulkhead at body 

station (BS) 1016, which could result in 

loss of the aft pressure bulkhead web 

and stiffeners, and consequent rapid 

decompression of the fuselage. 

Actions Since AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002), Was Issued 

Since 2010, we have received three 

reports of severe corrosion in the aft 

pressure bulkhead. Two of these 

airplanes were corroded completely 

through the thickness of the pressure 

web. The age of the airplanes when 

corrosion was found ranged from 12 to 

17 years. The total flight hours ranged 

from 40,892 to 68,389 hours, and the 

total flight cycles ranged from 22,701 to 

58,156 flight cycles. 

AD 2002–10–11, Amendment 39– 

12757 (67 FR 36085, May 23, 2002), 

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requires repetitive inspections for 

corrosion at 2-year intervals for 

airplanes having line numbers 1 through 

1042, and at 4-year intervals for 

airplanes having line numbers 1043 

through 3132. All reports of severe 

corrosion have been from the latter 

group of airplanes with the longer 

repetitive inspection interval. 

In addition, repair procedures in 

Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 

2000, which is specified in paragraph 

(g) of AD 2002–10–11, Amendment 39– 

12757 (67 FR 36085, May 23, 2002), as 

the appropriate source of service 

information, include instructions for 

blending out corrosion on the bulkhead 

web. The reworked web is more 

susceptible to subsequent corrosion. 

After consultation with the 

manufacturer, we have determined that 

reduction of the interval for the 

repetitive inspections from 4 years to 2 

years, together with removal of repair 

instructions for blending out corrosion 

on the bulkhead web, will reduce the 

frequency and severity of corrosion 

findings and provide an acceptable level 

of safety. 

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 retain all 

requirements of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002). This proposed AD would 

reduce the interval for the repetitive 

inspections for airplanes having line 

numbers (L/N) 1043 through 3132 

inclusive from 4 years to 2 years; and 

would provide an option to inspect only 

the aft side of the aft pressure bulkhead 

every 3 months for a maximum of 2 

years, at which time both the forward 

and aft sides of the aft pressure 

bulkhead would require repetitive 

inspections at 2-year intervals. This 

proposed AD would, for certain 

airplanes, add repetitive inspections of 

the frame chord drain path for debris, 

and corrective actions if necessary. 

Changes to AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002) 

This proposed AD would retain all 

the requirements of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002). Since AD 2002–10–11 

was issued, the AD format has been 

revised, and certain paragraphs have 

been rearranged. As a result, the 

corresponding paragraph identifiers 

have changed in this proposed AD, as 

listed in the following table: 

REVISED PARAGRAPH IDENTIFIERS

Requirement in AD 

2002–10–11, Amendment 39–12757 (67 

FR 36085, May 23, 

2002) 

Corresponding 

requirement in this 

proposed AD 

paragraph (a) paragraph (g) 

paragraph (b) paragraph (h) 

paragraph (c) paragraph (i) 

paragraph (d) paragraph (j) 

paragraph (e) paragraph (k) 

paragraph (f) paragraph (l) 

paragraph (g) paragraph (m) 

Note 2 (detailed inspection definition) 

in AD 2002–10–11, Amendment 39– 

12757 (67 FR 36085, May 23, 2002), has 

been removed from this proposed AD 

because it is described in Figure 1 of 

Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 

2000. 

Paragraph (e) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002), which is paragraph (k) 

in this proposed AD, has been revised 

to clarify that the required actions 

include inspecting the drain path in the 

chord frame for debris. 

The terminating action statement in 

paragraph (e)(1) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002), has been revised to 

terminate only the aft bulkhead 

inspection for cracking and corrosion in 

paragraph (g) of this proposed AD. 

Since we issued AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, 

May 23, 2002), Boeing Commercial 

Airplanes received an Organization 

Designation Authorization (ODA). We 

have revised this proposed AD to 

delegate the authority to approve an 

alternative method of compliance for 

any repair required by this AD to the 

Boeing Commercial Airplanes ODA 

rather than a Designated Engineering 

Representative. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 

2000, describes instructions on how to 

repair certain 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 ODA whom we 

have authorized to make those findings. 

This proposed AD would also reduce 

the repeat inspection interval for 

corrosion and cracking on airplanes 

having line numbers 1043 through 3132. 

Costs of Compliance 

We estimate that this proposed AD 

affects 419 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

ESTIMATED COSTS

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

Inspection ....................... 4 work-hours × $85 per hour = $340 per inspection cycle.$0 $340 per inspection 

cycle.

$142,460 per inspection 

cycle. 

The new requirements of this 

proposed AD add no additional 

economic burden. 

We estimate the following costs to do 

any necessary repairs that would be 

required based on the results of the 

proposed inspection. We have no way of 

determining the number of aircraft that 

might need these repairs: 

ON-CONDITION COSTS

Action Labor cost Parts cost Cost per product 

Repair ......................................... Up to 136 work-hours × $85 per hour = Up to $11,560 ............. $5,217 Up to $16,777. 

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49980 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 

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 proposed 

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 

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 that the 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 

removing airworthiness directive (AD) 

2002–10–11, Amendment 39–12757 (67 

FR 36085, May 23, 2002), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0694; Directorate Identifier 2013– 

NM–097–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by September 30, 2013. 

(b) Affected ADs 

This AD supersedes AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, certificated in any 

category, line numbers 1 through 3132 

inclusive. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by three reports of 

severe corrosion in the area affected by AD 

2002–10–11, Amendment 39–12757 (67 FR 

36085, May 23, 2002). We are issuing this AD 

to detect and correct corrosion or cracking of 

the aft pressure bulkhead, which could result 

in loss of the aft pressure bulkhead web and 

stiffeners, and consequent rapid 

decompression of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained Initial Aft Pressure Bulkhead 

Inspection 

This paragraph restates the requirements of 

paragraph (a) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with clarification of the drain path 

inspection. For Model 737 series airplanes 

having line numbers (L/N) 1 through 929 

inclusive, with more than 20,000 hours timein-service or 7 years since date of 

manufacture, whichever occurs first: Within 

120 days after January 20, 1986 (the effective 

date of AD 84–20–03 R1, Amendment 39– 

5183 (50 FR 51235, December 16, 1985)), 

unless already accomplished within the 21 

months before January 20, 1986, visually 

inspect the body station (BS) 1016 pressure 

bulkhead, including inspecting for cracking 

and corrosion of the pressure bulkhead, and 

for debris in the drain path in the chord 

frame, according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Revision 2, dated July 13, 

1984; or Revision 3, dated June 8, 2000. 

Remove any obstruction to the drain hole in 

the frame chord and replace any deteriorated 

leveling compound as noted in Boeing Alert 

Service Bulletin 737–53A1075, Revision 1, 

dated September 2, 1983; Revision 2, dated 

July 13, 1984; or Revision 3, dated June 8, 

2000. Treat the area of inspection with 

corrosion inhibitor BMS 3–23, or equivalent. 

After the effective date of this AD, use only 

Boeing Alert Service Bulletin 737–53A1075, 

Revision 3, dated June 8, 2000, to do the 

actions required by this paragraph. 

(h) Retained Drain Hole Enlargement 

This paragraph restates the requirements of 

paragraph (b) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised service bulletin 

requirements. For airplanes identified in 

paragraph (g) of this AD: Within 1 year after 

January 20, 1986 (the effective date of AD 84– 

20–03 R1, Amendment 39–5183 (50 FR 

51235, December 16, 1985)), accomplish the 

drain hole enlargement as shown in Boeing 

Alert Service Bulletin 737–53A1075, 

Revision 1, dated September 2, 1983; 

Revision 2, dated July 13, 1984; or Revision 

3, dated June 8, 2000. After the effective date 

of this AD, use only Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, to do the actions required by 

this paragraph. 

(i) Retained Corrective Action With Revised 

Compliance Methods 

This paragraph restates the requirements of 

paragraph (c) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised compliance methods. If 

cracking or corrosion is found during any 

inspection required by paragraph (g) or (j) of 

this AD: Before further flight, repair 

according to paragraph (i)(1) or (i)(2) of this 

AD, as applicable. 

(1) If the inspection was done before the 

effective date of this AD: Repair according to 

Boeing Alert Service Bulletin 737–53A1075, 

Revision 1, dated September 2, 1983; 

Revision 2, dated July 13, 1984; or Revision 

3, dated June 8, 2000. 

(2) If the inspection was done on or after 

the effective date of this AD: Repair using a 

method approved in accordance with the 

procedures specified in paragraph (p) of this 

AD. 

(j) Retained Repetitive Inspections Required 

by Paragraph (g) of This AD 

This paragraph restates the requirements of 

paragraph (d) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised actions. For airplanes 

identified in paragraph (g) of this AD: Repeat 

the visual inspections and corrosion inhibitor 

treatment specified in paragraph (g) of this 

AD at intervals not to exceed 2 years. 

Accomplishment of the initial aft pressure 

bulkhead inspection required by paragraph 

(k) of this AD terminates the inspection 

required by this paragraph. 

(k) Retained Aft Bulkhead Detailed 

Inspection 

This paragraph restates the requirements of 

paragraph (e) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised terminating action. Do a 

detailed inspection for cracking or corrosion 

of the aft pressure bulkhead at BS 1016 

(including the forward and aft sides of the 

pressure web, forward and aft sides of the 

pressure chord, pressure chord radius, 

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forward and aft sides of the angle stiffener, 

forward and aft chord, stringer end fitting, 

system penetration doublers, channel 

stiffeners and fasteners, ‘‘Z’’ stiffeners and 

fasteners, and fasteners common to the 

pressure chord and pressure web), according 

to Boeing Alert Service Bulletin 737– 

53A1075, Revision 3, dated June 8, 2000. Do 

this inspection at the applicable time shown 

in paragraph (k)(1), (k)(2), or (k)(3) of this AD. 

(1) For airplanes on which an inspection 

has previously been done according to the 

requirements of paragraph (g) of this AD: Do 

the inspection within 2 years since the most 

recent inspection according to paragraph (g) 

or (j) of this AD, as applicable. For the 

airplanes identified in paragraph (g) of this 

AD, accomplishment of the inspection 

required by paragraph (k) of this AD 

terminates the inspections for cracking and 

corrosion required by paragraph (j) of this 

AD. 

(2) For airplanes having L/Ns 930 through 

1042 inclusive, on which an inspection has 

not previously been done according to 

paragraph (g) of this AD: Do the inspection 

within 2 years after June 27, 2002 (the 

effective date AD 2002–10–11, Amendment 

39–12757 (67 FR 36085, May 23, 2002)). 

(3) For airplanes having L/Ns 1043 through 

3132 inclusive, on which an inspection has 

not previously been done according to 

paragraph (g) of this AD: Do the inspection 

within 6 years since the airplane’s date of 

manufacture, or within 2 years after June 27, 

2002 (the effective date AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002)), whichever occurs later. 

(l) Retained Repetitive Inspections 

This paragraph restates the requirements of 

paragraph (f) of AD 2002–10–11, Amendment 

39–12757 (67 FR 36085, May 23, 2002), with 

revised compliance times. Repeat the 

inspection in paragraph (k) of this AD at the 

applicable time shown in paragraph (l)(1) or 

(l)(2) of this AD. 

(1) For airplanes having L/Ns 1 through 

1042 inclusive: Repeat the inspection 

thereafter at intervals not to exceed 2 years. 

(2) For airplanes having L/Ns 1043 through 

3132 inclusive: Repeat the inspection 

thereafter within 2 years since the last 

inspection or within 120 days after the 

effective date of this AD, whichever occurs 

later. 

(m) Retained Repair 

This paragraph restates the requirements of 

paragraph (g) of AD 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), with revised repair requirements. If 

any corrosion or cracking is found during any 

inspection according to paragraph (k) or (l) of 

this AD: Do the applicable action specified in 

paragraph (m)(1) or (m)(2) of this AD. 

(1) If the inspection was done prior to the 

effective date of this AD: Before further flight, 

repair according to Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000. Exception: If corrosion or 

cracking of the web and stiffeners is outside 

the limits specified in Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, or if corrosion or cracking is 

found in any structure not covered by the 

repair instructions in Boeing Alert Service 

Bulletin 737–53A1075, Revision 3, dated 

June 8, 2000, before further flight, repair 

according to a method approved by the 

Manager, Seattle Aircraft Certification Office 

(ACO), or per data meeting the type 

certification basis of the airplane approved 

by the Boeing Commercial Airplanes 

Organization Designation Authorization 

(ODA) who has been authorized by the 

Manager, Seattle ACO, to make such 

findings. For a repair method to be approved 

by the Manager, Seattle ACO, as required by 

this paragraph, the Manager’s approval letter 

must specifically reference this AD. 

(2) After the effective date of this AD, if 

any corrosion or cracking is found during any 

inspection required by this AD: Before 

further flight, repair the corrosion or cracking 

using a method approved in accordance with 

the procedures specified in paragraph (p) of 

this AD. 

(n) New Drain Path Repetitive Inspection 

For airplanes having L/N 1 through 3132 

inclusive: Within 2 years since the last 

inspection in accordance with paragraph (k) 

of this AD or within 2 years after the effective 

date of this AD, whichever occurs later: Do 

a general visual inspection of the drain path 

in the chord frame for debris. Remove any 

obstruction to the drain hole in the frame 

chord and replace any deteriorated leveling 

compound. Treat the area of inspection with 

corrosion inhibitor BMS 3–23, or equivalent. 

Repeat the actions required by this paragraph 

at intervals not to exceed 2 years. Do all 

actions required by this paragraph in 

accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1075, Revision 3, dated June 8, 

2000. For the purposes of this AD, a general 

visual inspection is a visual examination of 

an interior or exterior area, installation, or 

assembly to detect obvious damage, failure, 

or irregularity. This level of inspection is 

made from within touching distance unless 

otherwise specified. A mirror may be 

necessary to ensure visual access to all 

surfaces in the inspection area. This level of 

inspection is made under normally available 

lighting conditions such as daylight, hangar 

lighting, flashlight, or droplight and may 

require removal or opening of access panels 

or doors. Stands, ladders, or platforms may 

be required to gain proximity to the area 

being checked. 

(o) New Optional Repetitive Aft Pressure 

Bulkhead Inspection for Certain Airplanes 

and Corrective Action 

For airplanes having L/Ns 1043 through 

3132 inclusive: In lieu of performing the 

inspection required by paragraph (l) of this 

AD, operators may do the actions specified 

in this paragraph. Within 2 years from the 

most recent aft pressure bulkhead inspection 

done as specified in Boeing Alert Service 

Bulletin 737–53A1075, Revision 1, dated 

September 2, 1983; Revision 2, dated July 13, 

1984; or Revision 3, dated June 8, 2000; or 

within 120 days after the effective date of this 

AD, whichever occurs later, do a detailed 

inspection for cracking or corrosion of the aft 

side of the aft pressure bulkhead at BS 1016 

(including the aft sides of the pressure web, 

aft sides of the pressure chord, pressure 

chord radius, aft chord, stringer end fitting, 

system penetration doublers, and fasteners 

common to the pressure chord and pressure 

web), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1075, Revision 3, 

dated June 8, 2000. If any corrosion or 

cracking is found: Before further flight, repair 

the corrosion or cracking using a method 

approved in accordance with the procedures 

specified in paragraph (p) of this AD. Repeat 

the inspection thereafter at intervals not to 

exceed 90 days. Within 2 years after the 

initial inspection done in accordance with 

this paragraph: Do the actions specified in 

paragraph (k) of this AD, and repeat 

thereafter at intervals not to exceed 2 years. 

(p) 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 2002–10–11, 

Amendment 39–12757 (67 FR 36085, May 23, 

2002), are approved as AMOCs for the 

corresponding provisions of this AD. 

(q) Related Information 

(1) 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) 917–6450; fax: (425) 917– 

6590; email: alan.pohl@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, 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. 

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49982 Federal Register / Vol. 78, No. 159 / Friday, August 16, 2013 / Proposed Rules 

Issued in Renton, Washington, on August 

9, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–19925 Filed 8–15–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0695; Directorate 

Identifier 2011–NM–264–AD] 

RIN 2120–AA64 

Airworthiness Directives; Saab AB, 

Saab Aerosystems 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 

Saab AB, Saab Aerosystems Model 340A 

(SAAB/SF340A) and SAAB 340B 

airplanes modified by Supplemental 

Type Certificate SA7971SW. This 

proposed AD was prompted by reports 

of smoke, a burning odor, and possible 

fire in the flight deck and cabin of the 

airplane, which was caused by brushes 

wearing beyond their limits, in the air 

conditioning motor. This proposed AD 

would require an inspection to 

determine if a certain air compressor 

motor is installed, an inspection to 

determine the age of a certain 

compressor hour meter since new or 

overhauled, and repetitive replacement 

of the brushes on affected air 

conditioning compressor motor units. 

As an option to the replacement, this 

proposed AD allows pulling the air 

conditioning circuit breaker and adding 

a placard. We are proposing this AD to 

detect and correct worn brushes 

contacting the commutator, which could 

result in a fire under the cabin floor 

with no means to detect or extinguish 

the fire. 

DATES: We must receive comments on 

this proposed AD by September 30, 

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. 

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: 

Gregory Thiele, Aerospace Engineer, 

Special Certification Office, ASW–190, 

FAA, 2601 Meacham Boulevard, Fort 

Worth, TX 76137; phone: (817) 222– 

5229; fax: (817) 222–5785; email: 

gregory.thiele@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– 

2013–0695; Directorate Identifier 2011– 

NM–264–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 smoke, a 

burning odor, and possible fire in the 

flight deck and cabin of the airplane, 

which was caused by brushes wearing 

beyond their limits, in the air 

conditioning motor. The rivets in the 

brush contacted the commutator, which 

caused sparks (the ignition source). The 

air conditioners (two units) are located 

under the floor, forward of the wing 

box. There is no fire detection or fire 

extinguishing equipment in the 

installed location. This condition (worn 

brushes contacting the commutator), if 

not corrected, could result in a fire 

under the cabin floor with no means to 

detect or extinguish the fire. 

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 these same 

type designs. 

Proposed AD Requirements 

This proposed AD would require an 

inspection to determine if a certain air 

compressor motor is installed, an 

inspection to determine the age of a 

certain compressor hour meter since 

new or overhauled, and repetitive 

replacement of the brushes on affected 

air conditioning compressor motor 

units. As an option to the replacement, 

this proposed AD allows pulling the air 

conditioning circuit breaker and adding 

a placard. This proposed AD also 

requires sending the inspection results 

to the FAA. 

This proposed AD contains detailed 

steps to address the unsafe condition 

rather than referring to service 

information. However, under the 

provisions of paragraph (p) of this 

proposed AD, operators may request 

approval of an alternative method of 

compliance (AMOC), if sufficient data 

are submitted to substantiate that the 

AMOC would provide an acceptable 

level of safety. 

Interim Action 

We consider this proposed AD 

interim action. The inspection reports 

that would be required by this proposed 

AD will enable us to obtain better 

insight into the nature, cause, and 

extent of the brush wear, and eventually 

to develop final action to address the 

unsafe condition. Once final action has 

been identified, we might consider 

further rulemaking. 

Costs of Compliance 

We estimate that this proposed AD 

affects 23 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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