Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules 72863 

Issued in Renton, Washington, on 

November 18, 2011. 

John P. Piccola, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–30603 Filed 11–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1250; Directorate 

Identifier 2010–NM–031–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 707–100 

long body, –200, –100B long body, and 

–100B short body series airplanes; 

Model 707–300, –300B, –300C, and 

–400 series airplanes; and Model 720 

and 720B series airplanes. For certain 

airplanes, this proposed AD would 

require using redefined flight cycle 

counts, determining the type of material 

of the horizontal stabilizer, rear spar, 

upper chords, and lower chords on the 

inboard and outboard ends of the rear 

spar; repetitively inspecting for cracking 

of the horizontal stabilizer components; 

and repairing or replacing the chord, or 

modification of chord segments made 

from 7079 aluminum, if necessary. For 

all airplanes, this proposed AD would 

require inspecting certain structurally 

significant items, and repairing 

discrepancies if necessary. This 

proposed AD was prompted by reports 

of stress corrosion cracking in the chord 

segments made from 7079 aluminum in 

the horizontal stabilizer rear spar, and 

fatigue cracking in the chord segments 

made from 7075 aluminum. We are 

proposing this AD to detect and correct 

stress corrosion and/or fatigue cracking 

in the horizontal stabilizer, which could 

compromise the structural integrity of 

the stabilizer. 

DATES: We must receive comments on 

this proposed AD by January 12, 2012. 

ADDRESSES: You may send comments 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: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590, 

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, Washington 98124– 

2207; telephone (206) 544–5000, 

extension 1; fax (206) 766–5680; email 

me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call (425) 227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office 

(ACO), 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6577; fax: (425) 917–6590, email: 

berhane.alazar@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–2011–1250; Directorate Identifier 

2010–NM–031–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://www.

regulations.gov, including any personal 

information you provide. We will also 

post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

We have received numerous reports of 

stress corrosion cracking in the chord 

segments made from 7079 aluminum in 

the Model 707 horizontal stabilizer rear 

spar. 7079 aluminum is known to be 

susceptible to stress corrosion cracking. 

Development of stress corrosion 

cracking was slowed by the 

accomplishment of the actions specified 

in Boeing 707 Service Bulletin 3356, 

Revision 2, dated December 12, 1991; 

and Boeing 707 Service Bulletin 3381, 

Revision 2, dated January 31, 1991. 

In addition, we have received three 

reports of fatigue cracking in the upper 

chords of the horizontal stabilizer rear 

spar near the side of the body. These 

chords are made from 7075 aluminum. 

In all three cases, the actions specified 

in Boeing 707/720 Service Bulletin 

A3313, Revision 1, dated May 27, 1977, 

had been incorporated. The fatigue 

cracking in either 7075 or 7079 material 

configuration has occurred early in the 

life of the modified structure. The 

fatigue cracks were generated by 

frequent training flights that included 

multiple touch-and-go cycles, which are 

most prevalent with military operators. 

These conditions, if not corrected, could 

result in stress corrosion and/or fatigue 

cracking in the horizontal stabilizer, 

which could compromise the structural 

integrity of the stabilizer. 

Parts made from 7079 aluminum have 

also been discovered on airplanes that 

were not originally delivered with those 

parts. Therefore, to adequately address 

the stress corrosion cracking in the 

chord segments in the rear spar of the 

horizontal stabilizer, it is necessary to 

determine the chord configuration on 

the airplane. Furthermore, it is also 

necessary to carefully maintain a record 

of that configuration until all chord 

segments of the rear spar of the 

horizontal stabilizers that are made from 

7079 aluminum have been removed 

from the fleet. Since horizontal 

stabilizers can be swapped, it is also 

necessary to implement the inspections 

for early fatigue cracking on all 

airplanes, regardless of their current 

usage. 

Relevant Service Information 

We have reviewed Boeing 707 Alert 

Service Bulletin A3515, dated December 


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19, 2007 (for Model 707 airplanes); and 

Boeing 707 Alert Service Bulletin 

A3516, dated April 4, 2008 (for Model 

707 airplanes, and Model 720 and 720B 

series airplanes). 

Boeing 707 Alert Service Bulletin 

A3515 describes procedures for the 

following actions: 

• Counting flight-cycles to determine 

the compliance times. 

• Determining the type of material of 

the horizontal stabilizer, rear spar, 

upper chords, and lower chords on the 

inboard and outboard ends of the rear 

spar. 

• Repetitive special detailed 

inspections for cracking of the upper 

chord on the inboard end of the rear 

spar of the left and right side horizontal 

stabilizers. 

• Repetitive high frequency eddy 

current inspections for cracking of the 

web flanges of the upper and lower 

chords of the rear spar of the left and 

right side horizontal stabilizers between 

stabilizer stations 92.55 and 272.55 for 

7079 aluminum components. 

• Repetitive low frequency eddy 

current inspections for cracking of the 

forward skin flanges of the upper and 

lower chords of the rear spar in the left 

and right side horizontal stabilizers 

from stabilizer stations –13.179 to 

272.55 (for lower chords) and 92.55 to 

272.55 (for upper chords) for 7079 

aluminum components. 

• Repetitive special detailed 

inspections for cracking of the upper 

chord of the inboard side of the rear 

spar in the left and right side horizontal 

stabilizers from stabilizer station 

–13.179 to 92.55 for 7079 aluminum 

components. 

• Replacing certain chord 

components made from 7079 aluminum. 

• Corrective actions, including 

replacing the chord(s) with a new chord 

and contacting Boeing for repair 

instructions and doing the repair. 

Boeing 707 Alert Service Bulletin 

A3516 specifies one-time inspections of 

certain structurally significant items, 

and provides procedures for counting 

flight cycles for determining the 

compliance times for the inspections. 

Related Rulemaking 

We issued AD 85–12–01, Amendment 

39–5073 (50 FR 26690, June 28, 1985), 

for Model 707 and 720 airplanes, as 

revised (AD 85–12–01 R1, Amendment 

39–5439 (51 FR 36002, October 8, 1986). 

That AD requires structural inspections 

and repairs or replacement on certain 

high time airplanes that have exceeded 

their fatigue design life. 

FAA’s Determination and Requirements 

of This Proposed AD 

We are proposing this AD because we 

evaluated all relevant information and 

determined the unsafe condition 

described previously is likely to exist or 

develop in other products of these same 

type designs. This proposed AD would 

require accomplishing the actions 

specified in the service information 

described previously, except as 

discussed below. The requirements of 

this proposed AD do not affect the 

requirements of AD 85–12–01 R1, 

Amendment 39–5439 (51 FR 36002, 

October 8, 1986). 

Differences Between the Proposed AD 

and Service Information 

Paragraph (i) of this proposed AD 

specifies determining the material of the 

structural components of the horizontal 

stabilizer in accordance with Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007. That service 

bulletin also specifies that this action be 

repeated. We have determined that 

accomplishing this action one time only 

will provide an adequate level of safety, 

provided that the component material is 

determined before further flight on any 

replaced horizontal stabilizer. 

Paragraph (i) of this proposed AD 

specifies a special detailed inspection of 

the upper chords, in accordance with 

Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007. That 

service bulletin specifies a compliance 

time of 180 days or 500 flight cycles 

(after the date on the service bulletin). 

This proposed AD, however, would 

remove the 500-flight-cycle compliance 

time to ensure that no airplane is 

unintentionally grounded, because it is 

possible an operator might exceed the 

flight-cycle grace period specified in 

paragraph (i) of this proposed AD before 

completing the inspection for chord 

material specified in paragraph (h) of 

this proposed AD. Similarly, paragraph 

(k) of this proposed AD removes the 

250- and 1000-flight-cycle compliance 

times (specified in Boeing 707 Alert 

Service Bulletin A3515, dated December 

19, 2007) for the initial inspection. This 

proposed AD would require these 

inspections within 180 days after the 

effective date of the AD. 

Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007, 

specifies to contact the manufacturer for 

instructions on how to repair certain 

conditions, but this proposed AD would 

require repairing those conditions in 

one of the following ways: 

• Using a method that we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Interim Action 

We consider this proposed AD 

interim action. If final action is later 

identified, we might consider further 

rulemaking then. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 10 airplanes of U.S. 

registry. The following table provides 

the estimated costs for U.S. operators to 

comply with this proposed AD. 

TABLE—ESTIMATED COSTS

Action Work hours 

Average 

labor rate 

per hour 

Parts Cost per product 

Number of 

U.S.-registered 

airplanes 

Fleet cost 

Inspections ................... 24 to 32 ........ $85 $0 $2,040 to $2,720 per 

inspection cycle.

10 $20,400 to $27,200 per 

inspection cycle. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 


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Federal Register / Vol. 76, No. 228 / Monday, November 28, 2011 / Proposed Rules 72865 

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. 

You can find our regulatory 

evaluation and the estimated costs of 

compliance in the AD Docket. 

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 AD: 

The Boeing Company: Docket No. FAA– 

2011–1250; Directorate Identifier 2010– 

NM–031–AD. 

Comments Due Date 

(a) We must receive comments by January 

12, 2012. 

Affected ADs 

(b) This AD affects AD 85–12–01, 

Amendment 39–5073 (50 FR 26690, June 28, 

1985), as revised by AD 85–12–01 R1, 

Amendment 39–5439, (51 FR 36002, October 

8, 1986). 

Applicability 

(c) This AD applies to The Boeing 

Company Model 707–100 long body, –200, 

–100B long body, and –100B short body 

series airplanes; Model 707–300, –300B, 

–300C, and –400 series airplanes; and Model 

720 and 720B series airplanes; certificated in 

any category; as identified in Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, and Boeing 707 Alert 

Service Bulletin A3516, dated April 4, 2008. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Unsafe Condition 

(e) This AD was prompted by reports of 

stress corrosion cracking in the chord 

segments made from 7079 aluminum in the 

horizontal stabilizer rear spar, and fatigue 

cracking in the chord segments made from 

7075 aluminum. The Federal Aviation 

Administration is issuing this AD to detect 

and correct stress corrosion and/or fatigue 

cracking in the horizontal stabilizer, which 

could compromise the structural integrity of 

the stabilizer. 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Flight Cycle Counting Procedure 

(g) Flight cycles, as used in this AD, must 

be counted as defined in Boeing 707 Alert 

Service Bulletin A3515, dated December 19, 

2007 (for Model 707 airplanes); or Boeing 707 

Alert Service Bulletin A3516, dated April 4, 

2008 (for Model 707 airplanes, and Model 

720 and 720B series airplanes). 

Determine Material of the Components of the 

Horizontal Stabilizer 

(h) For airplanes identified in Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007: At the earlier of the times 

specified in paragraphs (h)(1) and (h)(2) of 

this AD, determine the type of material of the 

horizontal stabilizer, rear spar, upper chords, 

and lower chords on the inboard and 

outboard ends of the rear spar, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007. 

(1) Within 180 days after the effective date 

of this AD. 

(2) Before further flight after any horizontal 

stabilizer is replaced after the effective date 

of this AD. 

Repetitive Inspections of 7075 Aluminum 

Components 

(i) For airplanes with horizontal stabilizer 

components made from 7075 aluminum, as 

determined during the inspection required by 

paragraph (h) of this AD: Within 180 days 

after the effective date of this AD, and before 

further flight after any replacement of the 

horizontal stabilizer, do a special detailed 

inspection for cracking of the upper chord on 

the inboard end of the rear spar in the left 

and right side horizontal stabilizers, from 

stabilizer station ¥13.179 to 92.55, in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007. Repeat the inspections 

thereafter at intervals not to exceed 500 flight 

cycles, and before further flight after any 

replacement of the horizontal stabilizer, 

except as provided by paragraph (j) of this 

AD. If any cracking is found, before further 

flight, either repair the cracking in 

accordance with Part 3 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, except as required by 

paragraph (n) of this AD; or replace the chord 

with a new chord, in accordance with Part 

6 of Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. 

Note 1: For the purposes of this AD, a 

special detailed inspection is ‘‘an intensive 

examination of a specific item, installation, 

or assembly to detect damage, failure, or 

irregularity. The examination is likely to 

make extensive use of specialized inspection 

techniques and/or equipment. Intricate 

cleaning and substantial access or 

disassembly procedure may be required. 

(j) For airplanes on which the chord is 

replaced with a new chord in accordance 

with Part 6 of the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007: 

Within 4,000 flight cycles after the chord 

replacement, do the inspections required by 

paragraph (i) of this AD, and repeat the 

inspections thereafter at the times specified 

in paragraph (i) of this AD. 

Repetitive Inspections of 7079 Aluminum 

Components 

(k) For airplanes with horizontal stabilizers 

that have components of the chords of the 

rear spar made from 7079 aluminum, as 

determined during the inspection required by 

paragraph (h) of this AD: Within 180 days 

after the effective date of this AD, do the 

actions required by paragraphs (k)(1), (k)(2), 

and (k)(3) of this AD, and repeat those 

actions at the applicable intervals specified 

in paragraphs (k)(1), (k)(2), and (k)(3) of this 

AD. 

(1) Do a special detailed inspection for 

cracking of the upper chord of the inboard 

side of the rear spar in the left and right side 

horizontal stabilizers from stabilizer station 

¥13.179 to 92.55, in accordance with Part 3 

of the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. Repeat the 

inspection thereafter at intervals not to 

exceed 250 flight cycles or 180 days, 

whichever occurs first. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, either repair 

the cracking, in accordance with Part 3 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, except as required by 

paragraph (n) of this AD; or replace the chord 

with a new chord, in accordance with Part 


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6 of Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. 

(2) Do a high frequency eddy current 

inspection for cracking of the web flanges of 

the upper and lower chords of the rear spar 

in the left and right side horizontal stabilizers 

from stabilizer stations 92.55 to 272.55, in 

accordance with Part 4 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007. Repeat the inspection 

thereafter at intervals not to exceed 1,000 

flight cycles or 180 days, whichever occurs 

first. If any cracking is found during any 

inspection required by this paragraph, before 

further flight, do the actions specified in 

paragraph (k)(2)(i) or (k)(2)(ii) of this AD. 

(i) Determine whether the cracking meets 

the limits specified in Part 4 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, and whether a previous 

repair has been done; determine if all 7079 

upper and lower chord segments installed on 

the horizontal stabilizer have had the Part II, 

Group 1, Preventative Modification specified 

in Boeing 707 Service Bulletin 3356 done; 

and do all applicable repairs and 

modifications, in accordance with Boeing 

707 Alert Service Bulletin A3515, dated 

December 19, 2007. Do the actions required 

by this paragraph in accordance with Part 4 

of the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007, except as required 

by paragraph (n) of this AD. Do all applicable 

repairs and modifications before further 

flight. 

(ii) Replace the chord with a new chord, 

in accordance with Part 6 of Boeing 707 Alert 

Service Bulletin A3515, dated December 19, 

2007. 

(3) Do low frequency eddy current (LFEC) 

inspections for cracking of the forward skin 

flanges of the upper and lower chords of the 

rear spar in the left and right side horizontal 

stabilizers from stabilizer stations ¥13.179 to 

272.55 (for lower chords) and 92.55 to 272.55 

(for upper chords), in accordance with Part 

5 of the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. Repeat the 

inspections thereafter at intervals not to 

exceed 1,000 flight cycles or 180 days, 

whichever occurs first. If any cracking is 

found during any inspection required by this 

paragraph, before further flight, do the 

actions specified in either paragraph (k)(3)(i) 

or paragraph (k)(3)(ii) of this AD. 

(i) Repair cracking, and determine whether 

all 7079 upper and lower chord segments 

installed on the horizontal stabilizer have 

had the Part II—Preventative Modification 

specified in Boeing 707 Service Bulletin 3381 

done, and do all applicable modifications, in 

accordance with Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007. Do 

the actions required by this paragraph in 

accordance with Part 5 of the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, except as required by 

paragraph (n) of this AD. Do all applicable 

modifications before further flight. 

(ii) Replace the chord with a new chord, 

in accordance with Part 6 of Boeing 707 Alert 

Service Bulletin A3515, dated December 19, 

2007. 

Modification/Chord Replacement 

(l) For airplanes identified in Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007, with horizontal 

stabilizers that have rear spar chord 

components made from 7079 aluminum and 

have not had embodied the modification of 

Part II of Boeing 707 Service Bulletin 3381, 

dated July 25, 1980; or Revision 1, dated July 

31, 1981: Before further flight after 

determining the type of material in 

accordance with paragraph (h) of this AD, 

modify all 7079 chord segments still installed 

on the horizontal stabilizer, in accordance 

with Part 5 of the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007; or 

replace the chord, in accordance with Part 6 

of the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. 

Supplemental Structural Inspection 

Document Inspections 

(m) For all airplanes: Within 180 days or 

1,000 flight cycles after the effective date of 

this AD, whichever occurs first, do the 

inspections of the applicable structurally 

significant items specified in and in 

accordance with the Accomplishment 

Instructions of Boeing 707 Alert Service 

Bulletin A3516, dated April 4, 2008. If any 

cracking is found, before further flight, repair 

in accordance with the procedures specified 

in paragraph (q) of this AD. The inspections 

required by AD 85–12–01 R1, Amendment 

39–5439 (51 FR 36002, October 8, 1986), are 

still required, except, as of the effective date 

of this AD, the flight-cycle interval for the 

repetitive inspections specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing 707 Alert 

Service Bulletin A3516, dated April 4, 2008, 

must be counted in accordance with the 

requirements of paragraph (g) of this AD. 

Exceptions to the Service Information 

(n) If any cracking is found during any 

inspection required by this AD, and Boeing 

707 Alert Service Bulletin A3515, dated 

December 19, 2007, specifies to contact 

Boeing for appropriate action: Before further 

flight, repair the cracking using a method 

approved in accordance with the procedures 

specified in paragraph (q) of this AD. 

(o) Where Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007, 

specifies that operators ‘‘refer to’’ NDT 

procedures, the procedures must be done in 

accordance with the service information 

identified in paragraphs (o)(1), (o)(2), and 

(o)(3) of this AD, as applicable. 

(1) Subject 51–00–00, ‘‘StructuresGeneral,’’ Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Part 6–Eddy 

Current, of the Boeing 707/720 

Nondestructive Test Manual, Document D6– 

48023, Revision 118, dated July 15, 2011. 

(2) Subject 55–10–07, ‘‘Horizontal 

Stabilizer,’’ of Part 6–Eddy Current, of the 

Boeing 707/720 Nondestructive Test Manual, 

Document D6–48023, Revision 118, dated 

July 15, 2011. 

(3) Subject 51–01–00, ‘‘Orientation and 

Preparation for Testing’’ of Part 1–General, of 

the Boeing 707/720 Nondestructive Test 

Manual, Document D6–48023, Revision 118, 

dated July 15, 2011. 

Parts Installation 

(p) As of the effective date of this AD, no 

person may install any horizontal stabilizer 

assembly with any chord segment having a 

part number other than that identified in 

paragraph 2.C.2. of Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 2007, on 

any airplane. 

Alternative Methods of Compliance 

(AMOCs) 

(q)(1) The Manager, Seattle Aircraft 

Certification Office, 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. 

Related Information 

(r) For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: (425) 917–6577; fax: (425) 917– 

6590; email: berhane.alazar@faa.gov. 

(s) 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; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

(425) 227–1221. 

Issued in Renton, Washington, on 

November 10, 2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–30582 Filed 11–25–11; 8:45 am] 

BILLING CODE 4910–13–P 


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