34096 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

Terminating Action

(b) Within 48 months after the effective

date of this AD: Do the actions required by

paragraphs (b)(1) and (b)(2), or (b)(3) of this

AD, per Boeing Alert Service Bulletin 747–

57A2312, dated June 15, 2000.

Accomplishment of the actions specified in

this paragraph constitutes terminating action

for the repetitive inspection requirements of

this AD.

(1) Perform an open-hole high frequency

eddy current (HFEC) inspection to detect

cracks, corrosion, or damage at the bolt hole

locations of the aft 10 taperlock fasteners in

the diagonal brace underwing fitting at the

Number 1 and Number 4 engine pylons per

Part 3 of the Accomplishment Instructions of

the service bulletin. If any cracking is

detected, before further flight, perform

applicable corrective actions per the service

bulletin, except as provided by paragraph (c)

of this AD.

(2) Before further flight: Replace all 10 aft

taperlock fasteners with new, improved

fasteners per Part 3 of the Accomplishment

Instructions of the service bulletin.

(3) Do an ultrasonic inspection to find

damaged fasteners per Part 2 of the

Accomplishment Instructions of the service

bulletin. Before further flight, replace all

damaged non-alloy steel and all alloy-steel

fasteners with new fasteners per Part 3 of the

Accomplishment Instructions of the service

bulletin. Do an open-hole HFEC inspection

before installation of the new fasteners; if any

cracking, corrosion, or damage is found,

before further flight, perform applicable

corrective actions per the service bulletin,

except as provided by paragraph (c) of this

AD.

Corrective Actions

(c) If any cracking, corrosion, or damage of

the bolt hole that exceeds the limits specified

in the service bulletin is found, or if any nonalloy steel bolt is found to be damaged,

during any inspection required by this AD,

and the bulletin specifies to contact Boeing

for appropriate action: Before further flight,

repair per a method approved by the

Manager, Seattle Aircraft Certification Office

(ACO), FAA; or per data meeting the type

certification basis of the airplane approved

by a Boeing Company Designated

Engineering Representative 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.

Spares

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

person shall install on any airplane, a

fastener, part number BACB30PE( ) * ( ); or

any other fastener made of 4340, 8740,

PH13–8 Mo or H–11 steel, in the locations

specified in this AD.

Alternative Methods of Compliance

(e) 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, Seattle

ACO. Operators shall submit their requests

through an appropriate FAA Principal

Maintenance Inspector, who may add

comments and then send it to the Manager,

Seattle ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

Special Flight Permits

(f) 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

(g) Except as provided by paragraph (c) of

this AD, the actions shall be done in

accordance with Boeing Alert Service

Bulletin 747–57A2312, dated June 15, 2000.

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 Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington 98124–

2207. 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.

Effective Date

(h) This amendment becomes effective on

August 1, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15933 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000–NM–212–AD; Amendment

39–12285; AD 2001–13–05]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Model BAe.125 Series 800A (C–29A

and U–125 Military), 1000A, and 1000B

Airplanes; Hawker 800 (U–125A

Military) Airplanes; and Hawker 800XP

and 1000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Raytheon Model

BAe.125 series 800A (C–29A and U–125

military), 1000A, and 1000B airplanes;

Hawker 800 (U–125A military)

airplanes; and Hawker 800XP and 1000

series airplanes, that requires removal of

existing clamps, bedding tapes, and

rubber connecting sleeves at the ends of

the turbine air discharge duct and the

water separator, and replacement of the

clamps and rubber connecting sleeves

with new, improved components. This

AD also requires, for certain airplanes,

removal of aluminum bedding strips

that are installed under the existing

clamps. The actions specified by this

AD are intended to prevent the turbine

air discharge duct or water separator

outlet duct from disconnecting from the

cold air unit turbine or from the water

separator, resulting in the loss of air

supply to maintain adequate cabin

pressure. Loss of adequate cabin

pressure at high altitude would require

emergency procedures, such as use of

oxygen, auxiliary pressurization, or

emergency descent.

DATES: Effective August 1, 2001.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 1,

2001.

ADDRESSES: The service information

referenced in this AD may be obtained

from Raytheon Aircraft Company,

Department 62, P.O. Box 85, Wichita,

Kansas 67201–0085. 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 FAA,

Wichita Aircraft Certification Office,

1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Paul

C. DeVore, Aerospace Engineer, Systems

and Propulsion Branch, ACE–116W,

FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100,

Mid-Continent Airport, Wichita, Kansas

67209; telephone (316) 946–4142; fax

(316) 946–4407.

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 certain Raytheon

Model BAe.125 series 800A (C–29A and

U–125 military), 1000A, and 1000B

airplanes; Hawker 800 (U–125A

military) airplanes; and Hawker 800XP

and 1000 series airplanes was published

as a supplemental notice of proposed

rulemaking (NPRM) in the Federal

Register on February 14, 2001 (66 FR

Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations 34097

10236). That action proposed to require

removal of existing clamps, bedding

tapes, and rubber connecting sleeves at

the ends of the turbine air discharge

duct and the water separator, and

replacement of the clamps and rubber

connecting sleeves with new, improved

components. That action also proposed

to include additional airplanes in the

applicability and to require, for certain

airplanes, removal of aluminum

bedding strips that are installed under

the existing clamps.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 270 Model

BAe.125 series 800A (C–29A and U–125

military), 1000A, and 1000B airplanes;

Hawker 800 (U–125A military)

airplanes; and Hawker 800XP and 1000

series airplanes of the affected design in

the worldwide fleet.

The FAA estimates that 154 airplanes

of U.S. registry will be affected by

paragraph (a) of this AD. We estimate

that the actions required by paragraph

(a) of this AD will take approximately 8

work hours per airplane to accomplish,

and that the average labor rate is $60 per

work hour. Required parts will cost

approximately $492 per airplane. Based

on these figures, the cost impact of this

AD on U.S. operators is estimated to be

$149,688, or $972 per airplane.

The FAA estimates that an additional

36 airplanes of U.S. registry will be

affected by paragraph (b) of this AD. We

estimate that the actions required by

paragraph (b) of this AD will take

approximately 2 work hours per

airplane to accomplish, and that the

average labor rate is $60 per work hour.

There is no cost for required parts.

Based on these figures, the cost impact

of paragraph (b) of this AD on U.S.

operators is estimated to be $4,320, or

$120 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the proposed requirements of this AD

action, and that no operator would

accomplish those actions in the future if

this AD were not adopted. The cost

impact figures discussed in AD

rulemaking actions represent only the

time necessary to perform the specific

actions actually required by the AD.

These figures typically do not include

incidental costs, such as the time

required to gain access and close up,

planning time, or time necessitated by

other administrative actions.

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:

2001–13–05 Raytheon Aircraft Company:

Amendment 39–12285. Docket 2000–

NM–212–AD.

Applicability: Model BAe.125 series 800A

(C–29A and U–125 military), 1000A, and

1000B airplanes; Hawker 800 (U–125A

military) airplanes, up to and including serial

number 258406; and Hawker 800XP series

airplanes, up to and including serial number

258483, and 1000 series airplanes;

certificated in any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

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 (d) 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 the turbine air discharge duct

or water separator outlet duct from

disconnecting from the cold air unit turbine

or from the water separator, resulting in the

loss of air supply to maintain adequate cabin

pressure, accomplish the following:

Replacement

(a) For Model BAe.125 series 800A (C–29A

and U–125 military) series airplanes; Hawker

800 (U–125A military) airplanes up to and

including serial number 258406; and Hawker

800XP series airplanes up to and including

serial number 258459: Remove the clamps,

bedding tapes, and rubber connecting sleeves

at the ends of the air turbine discharge duct

and the water separator, and replace the

clamps and rubber connecting sleeves with

new, improved components, in accordance

with the Accomplishment Instructions of

Raytheon Service Bulletin SB 21–3377,

Revision 1, dated July 2000, at the earliest of

the times specified in paragraphs (a)(1),

(a)(2), and (a)(3) of this AD.

(1) Prior to any extended over-water

operation.

(2) Within the next 300 hours time-inservice after the effective date of this AD.

(3) Within the next six months after the

effective date of this AD.

Note 2: An extended over-water operation

is defined in 14 CFR 1.1 as ‘‘* * * an

operation over water at a horizontal distance

of more than 50 nautical miles from the

nearest shoreline * * *.’’

(b) For Model Hawker 800XP series

airplanes having serial numbers 258460

through 258483; Model BAe.125 series

1000A/1000B airplanes; and Hawker 1000

series airplanes: Remove the aluminum

bedding strips from the air conditioning duct

sleeves attached to both ends of the turbine

air discharge duct and at the outlet end of the

water separator, in accordance with the

Accomplishment Instructions of Raytheon

Service Bulletin SB 21–3414, Revision 1,

dated July 2000, at the earliest of the times

specified in paragraphs (b)(1), (b)(2), and

(b)(3) of this AD.

(1) Prior to any extended over-water

operation.

(2) Within the next 300 hours time-inservice after the effective date of this AD.

(3) Within the next six months after the

effective date of this AD.

34098 Federal Register / Vol. 66, No. 124 / Wednesday, June 27, 2001 / Rules and Regulations

Actions Accomplished Previously and

Terminating Actions

(c) For certain airplanes, actions described

in the original issuance of Raytheon Service

Bulletin SB 21–3377 may have been

accomplished prior to the effective date of

this AD. On those airplanes, those actions are

not required to be repeated, as allowed by the

phrase, ‘‘unless accomplished previously.’’

However, any action described in Raytheon

Service Bulletin SB 21–3377, Revision 1,

dated July 2000; or Raytheon Service Bulletin

SB 21–3414, Revision 1, dated July 2000, that

has not been accomplished on those

airplanes must be accomplished in

accordance with this AD. Accomplishment of

the actions specified in both Raytheon

Service Bulletin SB 21–3377, Revision 1,

dated July 2000; and Raytheon Service

Bulletin SB 21–3414, Revision 1, dated July

2000, is considered to be terminating action

for the requirements of this AD.

Alternative Methods of Compliance

(d) 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, Wichita

Aircraft Certification Office (ACO), FAA.

Operators shall submit their requests through

an appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

Special Flight Permits

(e) 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

(f) The actions shall be done in accordance

with Raytheon Service Bulletin SB 21–3377,

Revision 1, dated July 2000; and Raytheon

Service Bulletin SB 21–3414, Revision 1,

dated July 2000. 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 Raytheon Aircraft Company,

Department 62, P.O. Box 85, Wichita, Kansas

67201–0085. Copies may be inspected at the

FAA, Transport Airplane Directorate, 1601

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

the FAA, Wichita Aircraft Certification

Office, 1801 Airport Road, Room 100, MidContinent Airport, Wichita, Kansas; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Effective Date

(g) This amendment becomes effective on

August 1, 2001.

Issued in Renton, Washington, on June 19,

2001.

Kalene C. Yanamura,

Acting Manager,, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 01–15932 Filed 6–26–01; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001–NM–193–AD; Amendment

39–12294; AD 2001–12–51]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 737–800 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This document publishes in

the Federal Register an amendment

adopting airworthiness directive (AD)

2001–12–51 that was sent previously to

all known U.S. owners and operators of

all Boeing Model 737–800 series

airplanes by individual notices. This AD

requires revising the Airplane Flight

Manual (AFM) to prohibit operating the

airplane at speeds in excess of 300 knots

indicated airspeed (KIAS) with

speedbrakes extended. This AD also

provides for optional terminating action

for the AFM revision. This action is

prompted by a report indicating that

severe vibration of the horizontal

stabilizer occurred on a Boeing Model

737–800 series airplane. The actions

specified by this AD are intended to

prevent severe vibration of the elevator

and elevator tab assembly following

deployment of the speedbrakes, which,

if not corrected, could result in severe

damage to the horizontal stabilizer,

followed by loss of controllability of the

airplane.

DATES: Effective July 2, 2001, to all

persons except those persons to whom

it was made immediately effective by

emergency AD 2001–12–51, issued June

13, 2001, which contained the

requirements of this amendment.

Comments for inclusion in the Rules

Docket must be received on or before

August 27, 2001.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 2001–NM–

193–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9 a.m. and 3 p.m.,

Monday through Friday, except Federal

holidays. Comments may be submitted

via fax to (425) 227–1232. Comments

may also be sent via the Internet using

the following address: 9-anmiarcomment@faa.gov. Comments sent

via fax or the Internet must contain

‘‘Docket No. 2001–NM–193–AD’’ in the

subject line and need not be submitted

in triplicate. Comments sent via the

Internet as attached electronic files must

be formatted in Microsoft Word 97 for

Windows or ASCII text.

Information pertaining to this

amendment may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Nancy H. Marsh, Aerospace Engineer,

Airframe Branch, ANM–120S, FAA,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2028; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION: On June

13, 2001, the FAA issued emergency AD

2001–12–51, which is applicable to all

Boeing Model 737–800 series airplanes.

Background

The FAA has received a report

indicating that severe vibration of the

horizontal stabilizer occurred on a

Boeing Model 737–800 series airplane.

The airplane was operating at an

altitude of 23,000 feet and an airspeed

of 320 knots indicated airspeed (KIAS).

This high frequency vibration was

initiated by deployment of the

speedbrakes during flight; it continued

unabated for approximately 40 seconds,

even though the speedbrakes were

retracted.

Results of post-event analysis and

investigation indicate that the type of

vibration of the elevator and elevator tab

assembly following deployment of the

speedbrakes, if not corrected, could

result in severe damage to the horizontal

stabilizer, followed by loss of

controllability of the airplane.

FAA’s Conclusions

In light of this information, the FAA

finds that certain new limitations

should be included in the FAAapproved Airplane Flight Manual

(AFM) for Model 737–800 series

airplanes to prohibit operating the

airplane at speeds in excess of 300 KIAS

with speedbrakes extended. The FAA

has determined that an airspeed of 300

KIAS provides an acceptable safety

margin compared to the 320–KIAS