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SERVICE BULLETIN

MANDATORY

Issued: June, 2013 SB 28-4127

The export of these commodities, technology or software are subject to the U.S. Export

Administration Regulations. Diversion contrary to U.S. law is prohibited. For guidance on

export control requirements, contact the Commerce Department's Bureau of Export

Administration at http://www.bis.doc.gov. 

Beechcraft Corporation (BC) issues Service Information for the benefit of owners and fixed

base operators in the form of two classes of Service Bulletins. The first class, Mandatory

Service Bulletins (red border) includes changes, inspection and modifications that could

affect safety or crashworthiness. BC also issues Service Bulletins with no red border which

are designated as either recommended or optional in the compliance section within the

bulletin. In the case of recommended Service Bulletins, BC feels the changes, modifications,

improvements or inspections will benefit the owner/operator and although highly

recommended, Recommended Service Bulletins are not considered mandatory at the time of

issuance. In the case of Optional Service Bulletins, compliance with the changes,

modifications, improvements or inspections is at the owner/operator's discretion.

Both classes are available on the web at http://pubs.hawkerbeechcraft.com and mailed to:

(a) Owners of record on the FAA Aircraft Registration Branch List and the BC

Safety of Flight Information (SOFI) List.

(b) Those having a publications subscription.

Information on Safety of Flight Information (SOFI) or subscription can be obtained through

the Beechcraft Corporation Technical Manual Distribution Center (TMDC). As Mandatory

Service Bulletins and Service Bulletins are issued, the Service Bulletin Master Index will be

updated and available online at http://pubs.beechcraft.com. Warranty will be allowed only

when specifically defined in the Service Bulletin and in accordance with BC Warranty Policy.

Unless otherwise designated, BC Mandatory Service Bulletins, Service Bulletins and BC Kits

are approved for installation on BC airplanes in original or BC modified configurations only.

BC Mandatory Service Bulletins, Service Bulletins and Kits may not be compatible with

airplanes modified by STC installations or modifications other than BC approved kits.

1. Planning Information

A. Effectivity

(1) Airplanes

Part 1 applies to the following airplanes: Model G58 Baron, Serials TH-2335, TH-2338 through 

TH-2348, TH-2351 through TH-2359, TH-2362 through TH-2366, TH-2369, and TH-2371. 

Part 2 applies to the following airplanes: Model G58 Baron, Serials TH-2336, TH-2337, TH-2349,

TH-2350, TH-2360, TH-2361, TH-2367, TH-2368, TH-2370, TH-2372 and TH-2373. 

If you are no longer in possession of the airplane, please forward this information to the present

owner.

(2) Spares

None.

B. Reason

This Service Bulletin is being issued to address a potential for fuel leakage. Beechcraft Corporation has

received reports of fuel leaks due to improper installation of fuel system components. Leakage into an area

with an ignition source can create potential for fire. Sufficient fuel leakage can lead to an imbalance

condition, which may affect airplane controllability.

C. Description

In Part 1, this Service Bulletin provides instructions to inspect, and replace if necessary, left and right fuel

system installations at the following locations: 

• The outboard wet wing interconnect area.

• The interconnects for the leading edge inboard fuel cell, the leading edge outboard fuel cell, and the 

center tank fuel cell. 

• Fuel plumbing connections in the wheel well and nacelle. 

In Part 2, this Service Bulletin provides instructions to inspect for proper torque on fuel system fittings

located in the nacelle. 

TITLE: FUEL - INSPECTION FOR CONDITION OF WING FUEL SYSTEM 
SERVICE BULLETIN

Issued: June, 2013 SB 28-4127

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MANDATORY

D. Compliance

An Airworthiness Directive will be requested on the matter covered by this Service Bulletin.

Beechcraft Corporation considers this to be a Mandatory Service Bulletin. It must be accomplished no later

than 20 flight hours or two months from issuance of this Service Bulletin, whichever occurs first. Until such

time as the Service Bulletin has been complied with, reference Safety Communique 332. 

E. Approval

The engineering data contained in this Service Bulletin is FAA approved. 

Prior to accomplishment, owners/operators of airplanes registered in countries other than the United

States shall consult with their local Aviation Regulatory Authority. 

Incorporation of this Service Bulletin restores the airplane to original Type Design. 

F. Manpower

The following information is for planning purposes only:

Estimated man-hours for inspection for Part 1: 30 hours

Estimated man-hours for inspection for Part 2: 4 hours

Estimated man-hours for installation/rework Part 1 only: 10 hours

Suggested number of technicians: 1

The above is an estimate based on experienced, properly equipped technicians complying with this

Service Bulletin. Occasionally, after work has started, conditions may be found that could result in

additional man-hours.

G. Weight and Balance

Negligible.

It is the responsibility of the owner/operator to maintain compliance with the applicable Airworthiness

Regulations.

H. Electrical Load Data

No change.

I. Software Accomplishment Summary

Not applicable.

J. References

Baron 55 and 58 Maintenance Manual, P/N 55-590000-13G5, Chapter 7, Chapter 20, Chapter 28, and

Chapter 32;

Safety Communique 332.
SERVICE BULLETIN

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SB 28-4127

MANDATORY

K. Publications Affected

It is recommended that a note “See Service Bulletin 28-4127” be made in the following:

Appropriate chapter of the applicable Airplane Maintenance Manual (AMM), Shop Manual, Flight Manual,

Flight Manual Supplement, and Illustrated Parts Catalog.

L. Interchangeability of Parts

Not applicable.

M. Warranty Credit 

Warranty credit for labor and parts to the extent noted under MANPOWER and MATERIAL will be allowed

on all airplanes meeting all the following criteria:

(1) Airplane owners must have active Standard Warranty coverage and/or an active Beechcraft

Maintenance program with applicable Service Bulletin coverage for the subject airplane when the

Service Bulletin is issued.

(2) Standard Warranty coverage and/or Beechcraft Maintenance Program with applicable Service

Bulletin coverage must be active for the subject airplane on the day the work is accomplished. 

(3) The work shall be accomplished in accordance with the criteria defined in Paragraph 1.D.,

COMPLIANCE. 

(4) The work shall be accomplished in accordance with criteria defined in Paragraph 3,

ACCOMPLISHMENT INSTRUCTIONS.

(5) The work shall be accomplished at Hawker Beechcraft Services or an Authorized Service Center

(ASC) rated to perform work on the specific model of Beechcraft airplane. 

(6) While work shall be accomplished in accordance with the criteria defined in Paragraph 1.D,

COMPLIANCE, warranty coverage offered in this Service Bulletin will expire 12 months from the last

day of the month this Service Bulletin is issued. After this date, the owner/operator assumes the

responsibility for compliance cost.

(7) Claims for compliance with this Service Bulletin (SB) are to be filed as a W3-type claim against SB

28-4127.

(8) After the Service Bulletin has been accomplished, a warranty claim must be submitted to Beechcraft

within 60 days of the Service Bulletin completion date. 

Beechcraft Corporation reserves the right to void continued airplane warranty coverage in the area

affected by this Service Bulletin until the date the Service Bulletin is accomplished.

The owner/operator should contact Hawker Beechcraft Services or an ASC to schedule the warranty work

to be accomplished. Hawker Beechcraft Services or an ASC must submit the appropriate paperwork

directly to the Beechcraft Warranty Department for warranty consideration.
SERVICE BULLETIN

Issued: June, 2013 SB 28-4127

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MANDATORY

2. Material Information

A. Materials - Price and Availability

Contact information:

Hawker Beechcraft Parts & Distribution (HBP&D)

10511 East Central Avenue

Wichita, KS 67206

USA

Phone: 316-676-3100 or 1-888-727-4344

Fax: 316-676-3222 or 316-676-3327

E-mail: HBC_Parts@beechcraft.com

B. Industry Support

Not applicable.

C. Airplanes

(1) The following parts required for accomplishment of Part 1 of this Service Bulletin may be ordered

through Hawker Beechcraft Services, an ASC, or HBP&D:

Part Number Description Quantity Per 

Airplane

60-921046-5 Leading Edge Outboard Bladder Bag, Left As Required

60-921046-6 Leading Edge Outboard Bladder Bag, Right As Required

002-920034-9 Leading Edge Inboard Bladder Bag, Left As Required

002-920034-10 Leading Edge Inboard Bladder Bag, Right As Required

58-380003-13 Center Tank Bladder Bag, Left As Required

58-380003-14 Center Tank Bladder Bag, Right As Required

4852SS305 or 52KS3 Clamp 4 or 8*

WWD82 Clamp As Required

NAS1924-114 or WWD114 Clamp As Required

2F1-3-41366 Flex Hose As Required

60-921047-1 Tube Assembly As Required

002-920020-1 Gasket 6

35-921502 Gasket 4

*Install clamps P/N 4852SS305 or P/N 52KS3 as defined in Paragraph 3 Accomplishment Instructions,

Steps (6)(b) and (6)(c).
SERVICE BULLETIN

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SB 28-4127

MANDATORY

Beechcraft Corporation expressly reserves the right to supersede, cancel and/or declare obsolete,

without prior notice, any parts or publications that may be referenced in this Service Bulletin.

(2) The following materials may be obtained locally:

D. Spares

Not applicable.

E. Reidentified Parts

None.

F. Tooling - Price and Availability 

Not applicable.

3. Accomplishment Instructions

This Service Bulletin shall be accomplished as follows:

NOTE

Should any difficulty be encountered in accomplishing this Service Bulletin,

contact Beechcraft Corporation at 1-800-429-5372 or 316-676-3140 for

commercial airplanes or contact appropriate headquarters for military airplanes. 

Observe all Warnings and Cautions contained in the airplane manuals

referenced in this Service Bulletin.

Whenever any part of this system is dismantled, adjusted, repaired or

renewed, detailed investigation must be made on completion to make sure

that distortion, tools, rags or any other loose articles or foreign matter that

could impede the free movement and safe operation of the system are not

present, and that the systems and installations in the work area are clean.

Part Number Description Quantity Per 

Airplane

Polyken 231 or ASTMD5486, Type IV, Class I Duct Tape As Required
SERVICE BULLETIN

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MANDATORY

A. Airplane

Part 1: Model G58 Baron, Serials TH-2335, TH-2338 through TH-2348, TH-2351 through TH-2359, TH-2362

through TH-2366, TH-2369, and TH-2371. 

At all locations during the incorporation of this Service Bulletin, inspect for

the existence of and damage from foreign objects (FOD). All foreign objects

shall be removed and any damage shall be addressed in accordance with

the Baron Maintenance Manual. 

(1) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting

reconnection of airplane electrical power.

Review fuel handling and fuel cell maintenance procedures warnings

contained in Baron Maintenance Manual, Chapter 28. 

(2) Defuel the airplane in accordance with Baron Maintenance Manual, Chapter 28-00-00-201. 

NOTE

After accomplishing the following procedures on the left side of the airplane,

repeat the procedures on the right side of the airplane. 

(3) Remove lower and upper access panels to enable inspection of the inboard, outboard, and center

section fuel cells. Refer to Figure 1. 

(4) Remove the respective fuel cell doors to gain access to the fuel cell bladders. These doors are

located behind access panels removed in Step (3). 

(5) Remove the exhaust heat shields to enable access to fuel cell. Refer to Figure 1. 

Inspection at Outboard Wet Wing Interconnect Area

Inspect for the existence of and damage from foreign objects. All foreign

objects shall be removed and any damage shall be addressed. 

(6) Locate tube assembly, P/N 60-921047-1, and the attached flex hose, P/N 2F1-3-41366, at 

the outboard wet wing interconnect area. Refer to Figure 2. Remove clamps, P/N 52KS3 or 

P/N 4852SS305, that are attached to flex hose P/N 2F1-3-41366. Remove the flex hose, 

P/N 2F1-3-41366 from the airplane. Refer to Figure 2. Inspect for and remove any debris (FOD).

Inspect for signs of damage (deformity that might prevent proper sealing) to the tube assembly, 

P/N 60-921047-1, or the flex hose (such as cuts or scarring) P/N 2F1-3-41366, and accomplish the

following:
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SB 28-4127

MANDATORY

(a) If tube assembly, P/N 60-921047-1, is deformed, thereby preventing proper sealing, remove the

tube assembly and install new tube assembly, P/N 60-921047-1. 

NOTE

In the following Steps (6)(b) and (6)(c), it is permissible to install a second clamp

at each end of the installed flex hose to ensure a complete seal. The additional

clamp must be clocked 90 degrees from the original. 

(b) If no damage (such as cuts or scarring) exists to the inside sealing surface of the existing flex

hose, install the flex hose and one (1) or two (2) new clamps P/N 52KS3 or P/N 4852SS305, as

needed, at each end of the hose. Torque to 20-25 inch-pounds. 

(c) If damage (such as cuts or scarring) exists to the inside sealing surface of the existing flex hose,

install new flex hose P/N 2F1-3-41366, and one (1) or two (2) new clamps, P/N 52KS3 or 

P/N 4852SS305, as needed, at each end of the hose. Torque to 20-25 inch-pounds. 

(d) Install any access panels that were removed. 

Inspection at Three Fuel Cells

Inspect for the existence of and damage from foreign objects. All foreign

objects shall be removed and any damage shall be addressed in accordance

with the Baron Maintenance Manual. 

Only slight force shall be applied to the nipple base during the following steps.

Damage to the bladder could occur if too much force is used.

(7) Use Figure 3, Figure 4, and Figure 5 to accomplish the following on the leading edge inboard

bladder, the leading edge outboard bladder, and the center tank bladder:

(a) Locate each of the two (2) P/N 002-920012-53 inboard (2-inch outside diameter) interconnect

tubes, and one (1) P/N 002-920012-51 outboard interconnect tube (3-inch outside diameter) that

connect the center tank fuel bladder to the leading edge inboard and outboard bladders. 

(b) Accomplish the following on the two (2) P/N 002-920012-53 inboard (2-inch outside diameter)

interconnect tubes, and one (1) P/N 002-920012-51 outboard interconnect tube (3-inch outside

diameter) that connect the center tank fuel bladder to the leading edge inboard and outboard

bladders:

Use an explosion-proof flashlight that meets criteria of MIL-F-3747, Type II

or III, Style 1 or 2.
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MANDATORY

(i) Using a (non-explosive) borescope and/or flashlight and mirror, visually inspect each fuel 

bladder interconnect nipple base reinforcement area for separation from bladder wall. 

Refer to Figure 5. If any degree of separation is noted, remove and replace fuel bladder. If 

no separation is noted, continue to next step.

(ii) The purpose of this step is to verify interconnect tube position relative to the spar. If the 

interconnect tube is not correctly positioned, unintended loads could be induced on the 

bladder. Remove the center tank fuel bladder nipple and clamps from each interconnect 

tube. Apply forward pressure to the aft side of each interconnect tube. If the interconnect 

tube(s) are installed correctly the tube bead should come against the spar and not 

continue into the leading edge fuel cell area (See Figure 4). If the interconnect tube is not 

installed correctly remove the interconnect tube and install correctly per Figure 4. If the 

tube is installed correctly continue to next step.

(iii) Along the lower accessible areas of the fuel bay liners, use a borescope to verify that duct 

tape is installed over rivets and sheet metal edges, and that no foreign objects are present. 

If any foreign objects exist or tape is found missing from edges, verify that no damage 

exists to the bladder. Install tape, if missing, over defined areas.

(iv) The purpose of this step is to verify that the bladder is positioned tight against the spar. If 

the bladder is not tight against and supported by the spar, unintended loads could be 

induced on the bladder. Hold forward pressure on the aft side of the interconnect tube(s), 

access the forward side of the interconnect tubes in the inboard and outboard leading 

edge bladders and ensure that the leading edge inboard and outboard fuel cells, at each 

interconnect tube, are tight against the forward side of the spar. If not tight, reposition 

nipple, ensuring it is tight against the forward face of the spar. 

(v) Reinstall center tank nipples to interconnect tubes and ensure that the bladder is tight 

against the aft face of the fuel bay liner. 

(vi) Install new clamps P/N WWD82, as applicable, to interconnect tube, P/N 002-920012-53. 

Ensure that the clamps are torqued to 30-35 inch-pounds. Install new clamps, 

P/N WWD114 (or equivalent P/N NAS1924-114), as applicable, to interconnect tube, 

P/N 002-920012-51. Ensure that the clamps are torqued to 35-40 inch-pounds. 

(c) Ensure that the hanger snap clips are properly fastened on the top of each fuel bladder. 

(d) Install the respective fuel cell doors, using new gaskets, P/N 002-920020-1 (Quantity 3 per wing)

and P/N 35-921502 (Quantity 2 per wing). Install fuel access panels. Install any other access

panels that were removed to gain access to the three fuel cells. Note: Do not install exhaust heat

shields at this time. 

Inspection of Wheel Well and Nacelle Area

Inspect for the existence of and damage from foreign objects. All foreign

objects shall be removed and any damage shall be addressed in accordance

with the Baron Maintenance Manual. 
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SB 28-4127

MANDATORY

(8) Reconnect the airplane battery and restore power. 

(9) Jack the airplane in accordance with Baron Maintenance Manual, Chapter 07-10-00-201.

(10) Partially retract the landing gear to allow inboard gear doors to fully open. Refer to Baron

Maintenance Manual, Chapter 32.

(11) Remove all power from the airplane and disconnect the battery. 

NOTE

The following Steps (12) through (14) apply to the left and right side of the

airplane. Step (15) applies to the left side of the airplane. Step (16) applies to the

right side of the airplane. 

(12) In the wheel well area depicted in general location Figure 6, verify torque on all fittings per Baron

Maintenance Manual, Chapter 20-10-00.

(13) Gain access to four (4) B-nuts in the lower nacelle area, between the aft engine firewall and leading

edge fuel bay. Refer to Figure 7. Verify that these four (4) B-nuts are torqued per Baron Maintenance

Manual, Chapter 20-10-00. 

(14) Locate the inboard lower nacelle fairing. Remove the fairing to expose the manifold pressure

transducer. Refer to Figure 8. One (1) B-nut is located at each end of the tube that runs from the

transducer to the firewall. Verify that each B-nut is torqued per Baron Maintenance Manual, Chapter

20-10-00. 

(15) Refer to Figure 9, Sheets 1 and 2. Gain access to the left upper nacelle area. Verify that eight (8) 

B-nuts are torqued per Baron Maintenance Manual, Chapter 20-10-00. 

(16) Refer to Figure 10 and gain access to the right upper nacelle area. Verify that two (2) B-nuts are

torqued per Baron Maintenance Manual, Chapter 20-10-00. 

(17) Reconnect the airplane battery and restore power. 

(18) Perform an electrical retraction and extension of the main landing gear to verify proper operation of

the landing gear. 

(19) Ensure that the landing gear is in the full down position. Check to be sure that all gears are in the

down and locked position. Refer to Baron Maintenance Manual, Chapter 32. 

(20) Remove the airplane from jacks. 

Final Check

(21) Fully fuel the airplane in accordance with the Baron Maintenance Manual, Chapter 28-00-00-201. A

minimum of four hours after fueling the airplane, check for leaks. 

(22) Leak check all fittings verified in Steps (12) through (16) with power applied and boost pump

selected to the High position. 

(23) Install any access covers that were removed in Steps (12) through (16), including the exhaust heat

shield, and verify that all access panels are installed. 

(24) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment.

(25) Return airplane to service.
SERVICE BULLETIN

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MANDATORY

Part 2: Model G58 Baron, Serials TH-2336, TH-2337, TH-2349, TH-2350, TH-2360, TH-2361, TH-2367, 

TH-2368, TH-2370, TH-2372 and TH-2373. 

(1) Remove all power from the airplane and disconnect the battery. Display warning notices prohibiting

reconnection of airplane electrical power.

NOTE

The following Steps (2) through (4) apply to the left and right side of the airplane.

Step (5) applies to the left side of the airplane. Step (6) applies to the right side of

the airplane. 

(2) Remove the exhaust heat shields to enable access to the aft portion of the nacelle. Refer to 

Figure 1. 

(3) Locate four (4) B-nuts in the lower nacelle area, between the aft engine firewall and leading edge

fuel bay. Refer to Figure 7. Verify that these four (4) B-nuts are torqued per Baron Maintenance

Manual, Chapter 20-10-00. 

(4) Locate the inboard lower nacelle fairing. Remove the fairing to expose the manifold pressure

transducer. Refer to Figure 8. One (1) B-nut is located at each end of the tube that runs from the

transducer to the firewall. Verify that each B-nut is torqued per Baron Maintenance Manual, Chapter

20-10-00. 

(5) Refer to Figure 9, Sheets 1 and 2. Gain access to the left upper nacelle area. Verify that eight (8) 

B-nuts are torqued per Baron Maintenance Manual, Chapter 20-10-00. 

(6) Refer to Figure 10 and gain access to the right upper nacelle area. Verify that two (2) B-nuts are

torqued per Baron Maintenance Manual, Chapter 20-10-00. 

(7) Reconnect the airplane battery and restore power. 

(8) Leak check all fittings verified in Steps (3) through (6) with power applied and boost pump selected

to the High position. 

(9) Install any access covers that were removed in Steps (2) through (6). 

(10) Ensure all work areas are clean and clear of tools and miscellaneous items of equipment.

(11) Return airplane to service.

B. Spares

Not applicable.

C. Record of Compliance

Upon completion of this Service Bulletin, make an appropriate maintenance record entry.
SERVICE BULLETIN

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SB 28-4127

MANDATORY

B412706.AI

LOWER ACCESS PANELS

UPPER ACCESS PANEL LOCATIONS

HEAT SHIELD 

SHOWN REMOVED

FUEL ACCESS 

Access Panel Locations

Figure 1
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MANDATORY

A

DETAILA B412702.AI

MAIN SPAR FACE

MAIN SPAR FACE

P/N 2F1-3-41366 FLEX HOSE - 1 EACH

P/N 52KS3 OR P/N 4852SS305 CLAMP,

AS DEFINED IN PARAGRAPH 3 

ACCOMPLISHMENT INSTRUCTIONS,

STEPS (6)(b) AND (6)(c).

P/N 60-921047-1

TUBE ASSEMBLY

CENTER TANK FUEL BLADDER

LEADING EDGE OUTBOARD BLADDER

LEADING EDGE INBOARD BLADDER

WET WING

(LEFT WING SHOWN, RIGHT OPPOSITE)

Inspection at Outboard Wet Wing Interconnect Area

Figure 2
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MANDATORY

B412703.AI

CENTER TANK FUEL BLADDER

LEADING EDGE OUTBOARD BLADDER

LEADING EDGE INBOARD BLADDER

WET WING

P/N 002-920012-53 

INBOARD INTERCONNECT TUBE

WWD82 CLAMP

(4 EACH - LEFT AND RIGHT)

P/N 002-920012-51 

OUTBOARD INTERCONNECT TUBE

WWD114 OR NAS1924-114 CLAMP

(2 EACH - LEFT AND RIGHT)

(LEFT WING SHOWN, RIGHT OPPOSITE)

Inspection at Three Fuel Cells

Figure 3
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MANDATORY

B412704.AI

THE MIDDLE BEAD OF THE INTERCONNECT TUBE SHOULD BE ON THE AFT SIDE OF THE SPAR. THE INTERCONNECT

TUBE SHOULD BE STICKING OUT OF THE NIPPLE ON BOTH SIDES FOR THE MID-BOARD AND INBOARD TUBES. THE 

OUTBOARD TUBE SHOULD BE FLUSH OR SLIGHTLY IN OR OUT DEPENDING ON TOLERANCES. 

VIEW SHOWING THE MIDDLE BEAD OF THE 

P/N 002-920012-51 OR -53 INTERCONNECT

TUBE LOCATED ON THE AFT SIDE OF THE

SPAR.

BEAD SHOULD BE LOCATED FIRMLY

AGAINST SPAR TO ALLOW PROPER 

FIT AT FUEL CELL INSTALLATION. 

FWD

A

B

B

A FOR THE -51 2.60 INCHES

FOR THE -53 3.00 INCHES

FOR THE -51 2.90 INCHES

FOR THE -53 4.80 INCHES

SPAR

FUEL BAY

LINER (REFERENCE DIMENSIONS ONLY)

Bladder Installation Requirements

Figure 4
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SB 28-4127

MANDATORY

B412707.AI

NIPPLE FLANGE 

SEPARATION AND DAMAGE

Nipple Flange Separation and Damage

Figure 5
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MANDATORY

NACELLE B412705.AI WHEEL WELL VIEW LOOKING FORWARD

(LEFT SHOWN, RIGHT OPPOSITE)

L NACELLE

70.340

W.S.

31.750

C

Nacelle and Wheel Well

Figure 6
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MANDATORY

B412708.AI

DETAIL VIEW - LOOKING UP AT B-NUT LOCATION

- INBOARD SIDE

DETAIL VIEW OF INBOARD SIDE B-NUT LOCATION 

- LOOKING UP AND INBOARD

DETAIL VIEW - LOOKING UP AT B-NUT LOCATION

- INBOARD SIDE

GENERAL LOCATIONAL VIEW -

LOOKING UP AND INBOARD AT

RIGHT NACELLE

FWD

INBD

B-Nut Locations in Right Nacelle

Figure 7
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MANDATORY

B412709.AI

DETAIL VIEW - LOOKING OUTBOARD AT INBOARD SIDE

MANIFOLD PRESSURE

TRANSDUCER

DETAIL VIEW - B-NUT LOCATION -

FORWARD OF LEADING EDGE FUEL BAY

GENERAL LOCATIONAL VIEW

FWD INBD

Nacelle B-Nut Locations at Manifold Pressure Transducer

Figure 8
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SB 28-4127

MANDATORY

FWD

INBD

DETAIL VIEW - LOOKING OUTBOARD AT LEFT SIDE DETAIL VIEW - LOOKING FORWARD AND

 SLIGHTLY DOWN - LEFT NACELLE B412710.AI

DETAIL VIEW - LOOKING INBOARD AT LEFT NACELLE ACCESS

GENERAL LOCATIONAL VIEW -

LOOKING FORWARD AT LEFT NACELLE ACCESS

 - PANELS REMOVED

Upper Left Nacelle B-Nut Locations

Figure 9, Sheet 1 of 2
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MANDATORY

B412711.AI

GENERAL LOCATIONAL VIEW -

UPPER LEFT NACELLE

DETAIL VIEW - 

LOOKING FORWARD AND INBOARD

 AT B-NUT LOCATIONS

FWD

INBD

Upper Left Nacelle B-Nut Locations

Figure 9, Sheet 2 of 2
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SB 28-4127

MANDATORY

DETAIL VIEW - LOOKING INBOARD B412712.AI

DETAIL VIEW - LOOKING INBOARD

GENERAL LOCATIONAL VIEW -

LOOKING FORWARD AND OUTBOARD

FWD

OUTBD

B-Nut Locations in Upper Right Nacelle

Figure 10