Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations 40985

submit their requests through an appropriate

FAA Principal Maintenance Inspector, who

may add comments and then send it to the

Manager, ECO.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the ECO.

Special Flight Permits

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference Material

(d) The actions required by this AD shall

be performed in accordance with the

following service documents:

Document No. Pages Revision Date

RB.211–72–C878 ................................................................................. 1–2 ............................. 1 ................................. December 10, 1999

3–4 ............................. Original ....................... November 19, 1999

Appendix .................... Original ....................... November 19, 1999

Total pages: 7.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Rolls-Royce plc, PO Box 31, Derby,

England; telephone: 011–44–1332–249428;

fax: 011–44–1332–249223. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

Effective Date of This AD

(e) This amendment becomes effective on

August 2, 2000.

Issued in Burlington, Massachusetts, on

June 21, 2000.

Mark C. Fulmer,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 00–16231 Filed 6–30–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 99–NM–196–AD; Amendment

39–11806; AD 2000–13–07]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A330 and A340 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A330 and A340 series airplanes. This

AD requires repetitive detailed visual

and ultrasonic inspections of the main

landing gear (MLG) to detect fatigue

cracks, and repair if necessary;

replacement of certain nose landing gear

(NLG) handwheel controllers and

certain placards with new placards;

installation of steering angle recording

software; and corrective action for

exceeding certain steering angles. This

AD also requires an AFM revision to

limit the nose wheel steering angle for

pushback and towing and to limit the

nose wheel steering for powered turns.

This amendment is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent MLG failure due to

fatigue cracking, which could result in

reduced structural capability of the

airplane and collapse of the MLG.

DATES: Effective August 7, 2000.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 7,

2000.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A330 and A340 series airplanes was

published in the Federal Register on

January 12, 2000 (65 FR 1833). That

action proposed to require repetitive

detailed visual and ultrasonic

inspections of the main landing gear

(MLG) to detect fatigue cracks, and

repair if necessary; replacement of

certain nose landing gear (NLG)

handwheel controllers and certain

placards with new placards; installation

of steering angle recording software;

corrective action for exceeding certain

steering angles; and an AFM revision to

limit the nose wheel steering angle for

pushback and towing and to limit the

nose wheel steering for powered turns.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comment received.

Request To Exclude Certain Airplanes

From Proposed Actions

The commenter (an operator) requests

that certain airplanes be excluded from

the actions specified in the proposed

AD. (Although the proposed rule

identifies no affected U.S.-registered

airplanes, the commenter has since

taken delivery of several Model A330

series airplanes.) Subsequent to

issuance of the proposed rule, the

manufacturer developed the following

production modifications for Model

A330 and A340 series airplanes (all of

which have been installed on the

commenter’s airplanes):

Modification 47487: Introduces scallop

on the growth main fitting of the main

landing gear (MLG)

Modification 47500: Introduces brake

steering and control unit (BSCU) S8D

for the MLG

Modification 47701: Provides for

application of markings for maximum

turning angle (±65 degrees) for towing

and pushback of the nose landing gear

doors

Modification 47787: Introduces ACMS

software to record nose wheel steering

angles exceeding 67 degrees during

towing and pushback

FAA Response

The FAA concurs with the request.

The Direction Ge ́ne ́rale de l’Aviation

40986 Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations

Civile (DGAC), which is the

airworthiness authority for France,

advises that the four production

modifications are acceptable alternative

means of compliance with all

requirements of the parallel French

airworthiness directives. Based on the

data presented, the FAA has revised the

applicability of the final rule to remove

the inspection and modification

requirements for airplanes on which all

four of the referenced production

modifications have been installed.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule with the change

described previously. The FAA has

determined that this change will neither

increase the economic burden on any

operator nor increase the scope of the

AD.

Cost Impact

None of the airplanes affected by this

action is on the U.S. Register. All

airplanes included in the applicability

of this rule currently are operated by

non-U.S. operators under foreign

registry; therefore, they are not directly

affected by this AD action. However, the

FAA considers that this rule is

necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register in the future.

Should an affected airplane be

imported and placed on the U.S.

Register in the future, it would require

approximately 1 work hour to inspect

the main landing gear; approximately 7

work hours to replace the controller;

approximately 1 work hour to replace

the placards; approximately 1 work

hour to install the software program;

and approximately 1 work hour to

revise the AFM. The average labor rate

is $60 per work hour. The manufacturer

has previously committed to bearing the

cost of the necessary parts to

accomplish the actions. Based on these

figures, the cost impact of the

inspections required by this AD would

be $60 per airplane, per inspection

cycle, and $660 per airplane for the

remaining actions.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Should an operator elect to modify

the functional software of the brake

steering and control unit (BSCU) rather

than replace the nose wheel steering

handwheel controllers, the modification

would take approximately 1 work hour.

Based on this figure, the cost impact of

the optional modification would be $60

per airplane.

Regulatory Impact

The regulations adopted herein 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. Therefore, it is

determined that this final rule does not

have federalism implications under

Executive Order 13132.

For the reasons discussed above, I

certify that this action (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); and (3)

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. A final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends part 39 of the

Federal Aviation Regulations (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. Section 39.13 is amended by

adding the following new airworthiness

directive:

2000–13–07 Airbus Industrie: Amendment

39–11806. Docket 99–NM–196–AD.

Applicability: Model A330 and A340 series

airplanes, certificated in any category, except

those on which Airbus Modifications 47487,

47500, 47701, and 47787 have been installed

in production.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise modified, altered, or repaired in

the area subject to the requirements of this

AD. For airplanes that have been modified,

altered, or repaired so that the performance

of the requirements of this AD is affected, the

owner/operator must request approval for an

alternative method of compliance in

accordance with paragraph (k) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or

repair on the unsafe condition addressed by

this AD; and, if the unsafe condition has not

been eliminated, the request should include

specific proposed actions to address it.

Compliance: Required as indicated, unless

accomplished previously.

To prevent main landing gear (MLG)

failure due to fatigue cracking, which could

result in reduced structural capability of the

airplane and collapse of the MLG,

accomplish the following:

Inspection of the MLG

(a) Prior to the accumulation of 800 total

landings on the MLG, or within 120 landings

after the effective date of this AD, whichever

occurs later, perform detailed visual and

ultrasonic inspections of the MLG to detect

fatigue cracks, as specified in either

paragraph (a)(1) or (a)(2) of this AD, as

applicable.

(1) For Model A330 series airplanes:

Accomplish the detailed visual and

ultrasonic inspections in accordance with

Airbus Service Bulletin A330–32A3088,

Revision 02, dated June 10, 1999.

Note 2: For the purposes of this AD, a

detailed visual inspection is defined as: ‘‘An

intensive visual examination of a specific

structural area, system, installation, or

assembly to detect damage, failure, or

irregularity. Available lighting is normally

supplemented with a direct source of good

lighting at intensity deemed appropriate by

the inspector. Inspection aids such as mirror,

magnifying lenses, etc., may be used. Surface

cleaning and elaborate access procedures

may be required.’’

Note 3: Detailed visual and ultrasonic

inspections accomplished prior to the

effective date of this AD in accordance with

Airbus Service Bulletin A330–32A3088,

dated October 16, 1998; or Revision 01, dated

November 20, 1998; are acceptable methods

of compliance for the inspection

requirements of paragraph (a)(1) of this AD.

(2) For Model A340 series airplanes:

Accomplish the detailed visual and

ultrasonic inspections in accordance with

Airbus Service Bulletin A340–32A4124,

Revision 01, dated November 20, 1998.

Note 4: Detailed visual and ultrasonic

inspections accomplished prior to the

effective date of this AD in accordance with

Airbus Service Bulletin A340–32A4124,

dated October 16, 1998, are acceptable

methods of compliance for the inspection

requirements of paragraph (a)(2) of this AD.

Repetitive Inspections

(b) If no crack is detected during the

inspection required by paragraph (a)(1) or

Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations 40987

(a)(2) of this AD: Repeat the detailed visual

and ultrasonic inspections thereafter at

intervals not to exceed 120 landings.

Corrective Actions

(c) If any cracking is detected during any

inspection required by paragraph (a) or (b) of

this AD: Prior to further flight, perform a

detailed magnetic particle inspection of the

MLG to detect fatigue cracks, in accordance

with Airbus Service Bulletin A330–32A3088,

Revision 02, dated June 10, 1999, or Airbus

Service Bulletin A340–32A4124, Revision 01,

dated November 20, 1998, as applicable; and

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate, or

the Direction Ge ́ne ́rale de l’Aviation Civile

(DGAC) (or its delegated agent). For a repair

method to be approved by the Manager,

International Branch, ANM–116, as required

by this paragraph, the Manager’s approval

letter must specifically reference this AD.

Reporting

(d) Within 10 days after accomplishing any

inspection required by paragraph (a), (b), or

(c) of this AD, report the inspection results

(both positive and negative) to Airbus

Industrie at fax 33(0) 5 61 93 32 73.

Information collection requirements

contained in this regulation have been

approved by the Office of Management and

Budget (OMB) under the provisions of the

Paperwork Reduction Act of 1980 (44 U.S.C.

3501 et seq.) and have been assigned OMB

Control Number 2120–0056.

Replacement of Nose Wheel Steering

Handwheel Controllers or Software

Modification

(e) Within 20 days after the effective date

of this AD, replace the nose wheel steering

handwheel controllers with new controllers,

or modify the functional software of the

brake steering and control unit (BSCU), as

specified in either paragraph (e)(1) or (e)(2)

of this AD, as applicable.

(1) For Model A330 series airplanes:

Replace the controllers in accordance with

Airbus Service Bulletin A330–32–3091,

Revision 01, dated December 2, 1998, or

modify the functional software of the BSCU

in accordance with Airbus Service Bulletin

A330–32–3092, Revision 02, dated June 10,

1999.

Note 5: Replacement of nose wheel steering

handwheel controllers with new controllers

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A330–32–3091, dated November 19,

1998, is an acceptable method of compliance

for the replacement requirements of

paragraph (e)(1) of this AD.

Note 6: Modification of the functional

software of the BSCU accomplished prior to

the effective date of this AD in accordance

with Airbus Service Bulletin A330–32–3092,

dated December 18, 1998; or Revision 01,

dated February 24, 1999; is an acceptable

method of compliance for the software

modification requirements of paragraph (e)(1)

of this AD.

(2) For Model A340 series airplanes:

Replace the controllers in accordance with

Airbus Service Bulletin A340–32–4128,

Revision 01, dated December 2, 1998, or

modify the functional software of the BSCU

in accordance with Airbus Service Bulletin

A340–32–4131, Revision 01, dated June 10,

1999.

Note 7: Replacement of nose wheel steering

handwheel controllers with new controllers

accomplished prior to the effective date of

this AD in accordance with Airbus Service

Bulletin A340–32–4128, dated November 19,

1998, is an acceptable method of compliance

for the replacement requirements of

paragraph (e)(2) of this AD.

Note 8: Modification of the functional

software of the BSCU accomplished prior to

the effective date of this AD in accordance

with Airbus Service Bulletin A340–32–4131,

dated February 24, 1999, is an acceptable

method of compliance for the software

modification requirements of paragraph (e)(2)

of this AD.

Replacement of Placards

(f) Within 20 days after the effective date

of this AD, replace the placards on the leftand right-hand sides of the aft mechanicallyoperated nose landing gear doors with new

placards, as specified in either paragraph

(f)(1) or (f)(2) of this AD, as applicable.

(1) For Model A330 series airplanes:

Replace placards in accordance with

Airbus Service Bulletin A330–32–3089,

dated November 2, 1998.

(2) For Model A340 series airplanes:

Replace placards in accordance with Airbus

Service Bulletin A340–32–4126, dated

November 2, 1998.

Installation of a Software Program

(g) Within 20 days after the effective date

of this AD, accomplish either paragraph (g)(1)

or (g)(2) of this AD, as applicable.

(1) For Model A330–200 series airplanes:

Install a software program that automatically

records all nose wheel steering angle

exceedance above 63 degrees into the Aircraft

Condition Monitoring System (ACMS) [i.e.,

modify the new setup database software by

adding the existing operator customized

version; and upload the setup database

software to the data management unit (DMU)]

in accordance with Airbus Service Bulletin

A330–31–3033, dated September 13, 1999.

(2) For Model A330–300 and Model A340

series airplanes: Install a software program

that automatically records all nose wheel

steering angle exceedance above 67 degrees

into the ACMS (i.e., modify the new setup

database software by adding the existing

operator customized version; and upload the

setup database software to the DMU) in

accordance with Airbus Service Bulletin

A330–31–3033, dated September 13, 1999

(for Model A330–300 series airplanes), or

Airbus Service Bulletin A340–31–4047,

dated September 13, 1999 (for Model A340

series airplanes); as applicable.

Incorporation of Ground and Crew

Operating Procedures

(h) Within 20 days after the effective date

of this AD, revise the Limitations Section of

the FAA-approved Airplane Flight Manual

(AFM) by inserting the procedures to

incorporate ground operating procedures to

limit the nose wheel steering angle for

pushback and towing and to limit nose wheel

steering for powered turns, in accordance

with Flight Operations TELEX (FOT)

999.0099/98, Revision 5, dated May 21, 1999.

Corrective Actions for Exceedance of Nose

Wheel Steering Angle

(i) For Model A330–200 series airplanes: If,

after 20 days from the effective date of this

AD, a 63-degree hand wheel steering is

exceeded, a 63 degrees is recorded on the

ACMS, or a 60-degree steering is exceeded

during towing or pushback, within 4

landings after each occurrence, accomplish

the actions required by paragraph (a) of this

AD.

(j) For Model A330–300 and Model A340

series airplanes: If, after 20 days from the

effective date of this AD, a 65-degree hand

wheel steering is exceeded, a 67 degrees is

recorded on the ACMS, or a 60-degree

steering is exceeded during towing or

pushback; within 4 landings after each

occurrence, accomplish paragraph (j)(1) and

(j)(2) of this AD, as applicable.

(1) Accomplish the actions required by

paragraph (a) of this AD.

(2) For airplanes on which Airbus

Modification 46804 has been accomplished:

Reinstall a positive stop and re-rig the tiller

as specified in either paragraph (j)(2)(i) or

(j)(2)(ii) of this AD, as applicable.

(i) For Model A330–300 series airplanes:

Reinstall a stop and re-rig in accordance with

Airbus Service Bulletin A330–32–3091,

Revision 01, dated December 2, 1998.

(ii) For Model A340 series airplanes:

Reinstall a stop and re-rig in accordance with

Airbus Service Bulletin A340–32–4128,

Revision 01, dated December 2, 1998.

Alternative Methods of Compliance

(k) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 9: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

Special Flight Permits

(l) Special flight permits may be issued in

accordance with sections 21.197 and 21.199

of the Federal Aviation Regulations (14 CFR

21.197 and 21.199) to operate the airplane to

a location where the requirements of this AD

can be accomplished.

Incorporation by Reference

(m) Except for the repair required by

paragraph (c) of this AD: The actions shall be

done in accordance with the following

Airbus service bulletins and telex, as

applicable.

40988 Federal Register / Vol. 65, No. 128 / Monday, July 3, 2000 / Rules and Regulations

Airbus service bulletin number Revision level Service bulletin date

A330–32A3088 ............................................................ 02 ................................................................................ June 10, 1999.

A340–32A4124 ............................................................ 01 ................................................................................ November 20, 1998.

A330–32–3091 ............................................................. 01 ................................................................................ December 2, 1998.

A330–32–3092 ............................................................. 02 ................................................................................ June 10, 1999.

A340–32–4128 ............................................................. 01 ................................................................................ December 2, 1998.

A340–32–4131 ............................................................. 01 ................................................................................ June 10, 1999.

A330–32–3089 ............................................................. Original ........................................................................ November 2, 1998.

A340–32–4126 ............................................................. Original ........................................................................ November 2, 1998.

A330–31–3033 ............................................................. Original ........................................................................ September 13, 1999.

A340–31–4047 ............................................................. Original ........................................................................ September 13, 1999.

Flight Operations TELEX 999.0099/98 ........................ Revision 5 ................................................................... May 21, 1999.

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 10: The subject of this AD is

addressed in French airworthiness directives

1998–475–103(B)R1; 1998–473–083(B)R1;

and 1999–160–096(B); all dated April 21,

1999.

(n) This amendment becomes effective on

August 7, 2000.

Issued in Renton, Washington, on June 22,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–16357 Filed 6–30–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–SW–18–AD; Amendment

39–11805; AD 2000–13–06]

RIN 2120–AA64

Airworthiness Directives; Sikorsky

Model S–61 Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD)

for Sikorsky Model S–61 helicopters.

That AD requires inspecting certain

pylon upper and lower hinge web

fittings (web fittings) for corrosion or a

crack and either repairing certain web

fittings or replacing any unairworthy

web fittings with airworthy web fittings.

That AD also requires creating a log card

or equivalent record and implementing

a recurring inspection of the web

fittings. This amendment retains the

requirements of that AD but corrects an

error in paragraph (a)(3) by removing

the words ‘‘and 3.E.’’ This amendment

is prompted by an operator notifying the

FAA of that error which requires an

unnecessary major inspection within 25

hours time-in-service (TIS). The actions

specified in this AD are intended to

remove an undue burden on the public

by superseding the AD and removing

the requirement for the major inspection

within 25 hours TIS.

DATES: Effective July 18, 2000.

The incorporation by reference of

certain publications listed in the

regulations was approved previously by

the Director of the Federal Register as of

March 30, 2000 (65 FR 13877, March 15,

2000).

Comments for inclusion in the Rules

Docket must be received on or before

September 1, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Regional Counsel, Southwest Region,

Attention: Rules Docket No. 2000–SW–

18–AD, 2601 Meacham Blvd., Room

663, Fort Worth, Texas 76137. You may

also send comments electronically to

the Rules Docket at the following

address: 9–asw–adcomments@faa.gov.

The service information referenced in

this AD may be obtained from Sikorsky

Aircraft Corporation, Attn: Manager,

Commercial Tech Support, 6900 Main

Street, P. O. Box 9729, Stratford,

Connecticut 06497–9129, phone (203)

386–7860, fax (203) 386–4703. This

information may be examined at the

FAA, Office of the Regional Counsel,

Southwest Region, 2601 Meacham

Blvd., Room 663, Fort Worth, Texas

76137; or at the Office of the Federal

Register, 800 North Capitol Street, NW.,

suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Brian K. Murphy, Aviation Safety

Engineer, ANE–150, 12 New England

Executive Park, Burlington, MA 01803,

telephone (781) 238–7739, fax (781)

238–7199.

SUPPLEMENTARY INFORMATION: On March

6, 2000, the FAA issued AD 2000–05–

16, Amendment 39–11626 (65 FR

13877, March 15, 2000). That AD for

Sikorsky Model S–61 helicopters with

pylon, part number (P/N) S6120–76265–

001 or S6120–76266–507, installed,

requires inspecting and repairing or, if

necessary, replacing certain web fittings

and the fitting faying surfaces. The AD

also requires making an entry on the log

card or equivalent record. That action

was prompted by the discovery of

extensive cracking in the area of the web

fitting. That condition, if not corrected,

could result in structural failure of

certain web fittings due to stress

corrosion, subsequent structural failure

of the tailboom and loss of control of the

helicopter.

Since the issuance of that AD, an

operator notified the FAA of an error.

That error is the reference in paragraph

(a)(3) of the AD to paragraph 3.E. of the

Accomplishment Instructions of

Sikorsky Aircraft Corporation Alert

Service Bulletin No. 61B20–33, dated

September 3, 1999 (ASB). Requiring

paragraph 3.E. of the ASB in paragraph

(a)(3) of the AD would inadvertently

require conducting a major inspection

within 25 hours TIS, which is not

intended. The Inspection Plan in Chart

A of the ASB refers to paragraph 3.E.,

which specifies a major recurring

inspection at 9000 flight hours or 4

years, whichever is less. That inspection

is appropriately covered under

paragraph (a)(6) of the AD, which

requires entering on the log card or

equivalent record the recurring

inspection intervals in accordance with

Chart A of the ASB.

Since requiring the major inspection

within 25 hours TIS is not required to

correct the unsafe condition, this AD

supersedes AD 2000–05–16. This AD

would correct the requirement that

inadvertently requires conducting the

major inspection in 25 hours TIS by

removing the words ‘‘and 3.E.’’ from

paragraph (a)(3) of the AD. The short