This section of the FEDERAL REGISTER

contains regulatory documents having general

applicability and legal effect, most of which

are keyed to and codified in the Code of

Federal Regulations, which is published under

50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by

the Superintendent of Documents. Prices of

new books are listed in the first FEDERAL

REGISTER issue of each week.

Rules and Regulations Federal Register

55681 

Vol. 77, No. 176 

Tuesday, September 11, 2012 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1250; Directorate 

Identifier 2010–NM–031–AD; Amendment 

39–17176; AD 2012–17–13] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting 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. 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 potential early 

fatigue cracking in the chord segments 

made from 7075 aluminum. For certain 

airplanes, this AD requires using 

redefined flight cycle counts, 

determining the type of material of the 

horizontal stabilizer, rear spar, and 

upper 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 

modifying chord segments made from 

7079 aluminum, if necessary. For all 

airplanes, this AD requires inspecting 

certain structurally significant items, 

and repairing discrepancies if necessary. 

We are issuing this AD to detect and 

correct stress corrosion and/or potential 

early fatigue cracking in the horizontal 

stabilizer, which could compromise the 

structural integrity of the stabilizer. 

DATES: This AD is effective October 16, 

2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of October 16, 2012. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P.O. Box 3707, 

MC 2H–65, Seattle, Washington 98124– 

2207; telephone 206–544–5000, 

extension 1; fax 206–766–5680; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://www.regulations.

gov; or in person at the Docket 

Management Facility between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

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: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM published in the Federal 

Register on November 28, 2011 (76 FR 

72863). For certain airplanes, that 

NPRM proposed to require using 

redefined flight cycle counts, 

determining the type of material of the 

horizontal stabilizer, rear spar, and 

upper 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 

modifying the chord segments made 

from 7079 aluminum, if necessary. For 

all airplanes, that NPRM also proposed 

to require inspecting certain structurally 

significant items, and repairing 

discrepancies if necessary. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comment 

received on the proposal (76 FR 72863, 

November 28, 2011) and the FAA’s 

response. 

Request To Correct Certain Fatigue 

Cracking Assertions 

Boeing reported that the NPRM (76 FR 

72863, November 28, 2011), in various 

locations, stated incorrectly that fatigue 

cracking occurred in rear spar chords 

made from 7075 aluminum. According 

to Boeing, fatigue cracking has been 

reported in spar chords made from 7079 

aluminum only. Boeing requested that 

we revise the NPRM to remove reference 

to ‘‘fatigue cracking’’ when addressing 

the failure mode of the rear spar chords 

made from 7075 aluminum. 

We partially agree with the request. 

Chords made from 7075 aluminum have 

better fatigue characteristics than those 

made from 7079 aluminum. But all 

metals fatigue to a varying degree. We 

have therefore revised this final rule to 

characterize these conditions as 

‘‘potential early fatigue’’ to address 

Boeing’s concern and clarify that the 

accelerated fatigue occurrence was a 

consequence of abnormal use of the 

airplane as used in military touch-andgo training. 

Additional Change Made to This AD 

Note 1 to paragraph (i) of the NPRM 

(76 FR 72863, November 28, 2011) 

defined a special detailed inspection. 

We have removed that note in this final 

rule. A special detailed inspection is 

defined in Boeing 707 Alert Service 

Bulletin A3515, dated December 19, 

2007, and it is unnecessary to repeat 

that definition in the AD. 

Conclusion 

We reviewed the relevant data, 

considered the comment received, and 

determined that air safety and the 

public interest require adopting the AD 


sroberts on DSK5SPTVN1PROD with RULES
55682 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 

with the changes described previously 

and minor editorial changes. We have 

determined that these minor changes: 

• Are consistent with the intent that 

was proposed in the NPRM (76 FR 

72863, November 28, 2011) for 

correcting the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (76 FR 72863, 

November 28, 2011). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of the AD. 

Interim Action 

We consider this AD interim action. If 

final action is later identified, we might 

consider further rulemaking then. 

Costs of Compliance 

We estimate that this AD affects 10 

airplanes of U.S. registry. The following 

table provides the estimated costs for 

U.S. operators to comply with this 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 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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2012–17–13 The Boeing Company: 

Amendment 39–17176; Docket No. 

FAA–2011–1250; Directorate Identifier 

2010–NM–031–AD. 

(a) Effective Date 

This AD is effective October 16, 2012. 

(b) Affected ADs 

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). 

(c) Applicability 

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. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

(e) Unsafe Condition 

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 potential early 

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 potential 

early fatigue cracking in the horizontal 

stabilizer, which could compromise the 

structural integrity of the stabilizer. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Flight Cycle Counting Procedure 

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 airplanes); or Boeing 707 

Alert Service Bulletin A3516, dated April 4, 

2008 (for Model airplanes, and Model 720 

and 720B series airplanes). 

(h) Determination of Material of the 

Components of the Horizontal Stabilizer 

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. 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 55683 

(2) Before further flight after any horizontal 

stabilizer is replaced after the effective date 

of this AD. 

(i) Repetitive Inspections of 7075 Aluminum 

Components 

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 on both 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 the Accomplishment Instructions of 

Boeing 707 Alert Service Bulletin A3515, 

dated December 19, 2007. 

(j) Repetitive Inspections on Airplanes With 

Replaced Chord 

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. 

(k) Repetitive Inspections of 7079 Aluminum 

Components 

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 of both 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 

6 of the Accomplishment Instructions 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 the 

Accomplishment Instructions of 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 the 

Accomplishment Instructions 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 any cracking, 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 the Accomplishment 

Instructions of 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 the 

Accomplishment Instructions of Boeing 707 

Alert Service Bulletin A3515, dated 

December 19, 2007. 

(l) Modification/Chord Replacement 

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 Boeing 707 Service 

Bulletin 3381, 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 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. 

(m) Supplemental Structural Inspection 

Document Inspections 

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. 

(n) Exception to the Service Information: 

Contacting FAA for Crack Repair 

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) Exception to the Service Information: 

Certain Compliance Procedures 

Where Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007, specifies 

that operators ‘‘refer to’’ nondestructive test 

(NDT) procedures, the procedures must be 

done in accordance with the service 


sroberts on DSK5SPTVN1PROD with RULES
55684 Federal Register / Vol. 77, No. 176 / Tuesday, September 11, 2012 / Rules and Regulations 

information identified in paragraphs (o)(1), 

(o)(2), and (o)(3) of this AD, as applicable. 

(1) Figure 20, ‘‘Electrical Conductivity 

Measurement for Aluminum,’’ of Subject 51– 

00–00, ‘‘Structures-General,’’ 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. 

(p) Parts Installation Prohibition 

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. 

(q) 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. 

(r) Related Information 

For more information about this AD, 

contact Berhane Alazar, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

ACO, 1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425–917– 

6577; fax: 425–917–6590; email: 

berhane.alazar@faa.gov. 

(s) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on October 16, 2012. 

(i) Boeing 707 Alert Service Bulletin 

A3515, dated December 19, 2007. 

(ii) Boeing 707 Alert Service Bulletin 

A3516, dated April 4, 2008. 

(iii) Subject 51–00–00, ‘‘Structures— 

General,’’ 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. The 

revision level of this document is identified 

in only the manual revision Transmittal 

Sheet. 

(iv) 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. The revision level of this 

document is identified in only the manual 

revision Transmittal Sheet. 

(v) 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. The revision level of this 

document is identified in only the manual 

revision Transmittal Sheet. 

(4) 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. 

(5) You may review copies of the 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. 

(6) You may also review copies of the 

service information that is incorporated by 

reference at the National Archives and 

Records Administration (NARA). For 

information on the availability of this 

material at NARA, call 202–741–6030, or go 

to: http://www.archives.gov/federal-register/ 

cfr/ibr-locations.html. 

Issued in Renton, Washington, on August 

24, 2012. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2012–21533 Filed 9–10–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0927; Directorate 

Identifier 2012–SW–052–AD; Amendment 

39–17178; AD 2012–18–02] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model AB412 and 

AB412 EP helicopters with certain hoist 

hook assemblies (hook) installed. This 

AD requires inspecting the hook for 

correct assembly of the nut and body. 

This AD is prompted by a report that a 

hook separated from the cable of a 

helicopter. These actions are intended 

to prevent detachment of the hook from 

the helicopter and subsequent loss of an 

external load, possibly resulting in 

personal injury. 

DATES: This AD becomes effective 

September 26, 2012. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of September 26, 2012. 

We must receive comments on this 

AD by November 13, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

http://www.regulations.gov. Follow the 

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments 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 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address 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 Operations Office between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this AD, any comments 

received, and other information. The 


sroberts on DSK5SPTVN1PROD with RULES